Relevant bibliographies by topics / Nanosatellites – Control systems

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Nanosatellites – Control systems'

Author: Grafiati
Published: 4 June 2021
Last updated: 16 February 2022

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Journal articles on the topic "Nanosatellites – Control systems"

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Wang, Yu, Oleg V. Denisov, and Liliana V. Denisova. "Simulation of the thermal control system of nanosatellite using the loop heat pipes under the orbital flight conditions." RUDN Journal of Engineering Researches 22, no. 1 (August 27, 2021): 23–35. http://dx.doi.org/10.22363/2312-8143-2021-22-1-23-35.

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One of the key problems in the development of nanosatellites is to provide a given temperature range for the operation of the on-board computer. The constantly increasing information load leads to the need to use more advanced processors with high thermal design power (TDP). The indicated thermal regime of processors can be achieved using remote heat removal systems - miniature loop heat pipes. Using a model of nanosatellite as an example, a thermal control system with miniature loop heat pipes is designed. The simulation was carried out in the Siemens NX program in the elliptical and geostationary orbits of the Earth. The cooling schemes of the processor with a thermal power of 15 W using one and two loop heat pipes are considered. Calculations showed that the use of loop heat pipes can reduce the processor temperature to acceptable values. The anisotropy of the thermal conductivity coefficient in the reinforcement plane of the composite material of the nanosatellite case can have a significant effect on the temperature of the processor. This opens up prospects for the use of anisotropic composite materials to ensure the thermal regime of the nanosatellite.
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Modenini, Dario, Anton Bahu, Giacomo Curzi, and Andrea Togni. "A Dynamic Testbed for Nanosatellites Attitude Verification." Aerospace 7, no. 3 (March 18, 2020): 31. http://dx.doi.org/10.3390/aerospace7030031.

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To enable a reliable verification of attitude determination and control systems for nanosatellites, the environment of low Earth orbits with almost disturbance-free rotational dynamics must be simulated. This work describes the design solutions adopted for developing a dynamic nanosatellite attitude simulator testbed at the University of Bologna. The facility integrates several subsystems, including: (i) an air-bearing three degree of freedom platform, with automatic balancing system, (ii) a Helmholtz cage for geomagnetic field simulation, (iii) a Sun simulator, and (iv) a metrology vision system for ground-truth attitude generation. Apart from the commercial off-the-shelf Helmholtz cage, the other subsystems required substantial development efforts. The main purpose of this manuscript is to offer some cost-effective solutions for their in-house development, and to show through experimental verification that adequate performances can be achieved. The proposed approach may thus be preferred to the procurement of turn-key solutions, when required by budget constraints. The main outcome of the commissioning phase of the facility are: a residual disturbance torque affecting the air bearing platform of less than 5 × 10−5 Nm, an attitude determination rms accuracy of the vision system of 10 arcmin, and divergence of the Sun simulator light beam of less than 0.5° in a 35 cm diameter area.
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Phylonin, Oleg, Igor Belokonov, and Peter Nikolaev. "Traffic Control Systems of Nanosatellites in the Zone of the International Space Station." Procedia Engineering 185 (2017): 380–87. http://dx.doi.org/10.1016/j.proeng.2017.03.319.

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Veres, S. M., S. B. Gabriel, D. Q. Mayne, and E. Rogers. "Analysis of Formation Flying Control of a Pair of Nanosatellites." Journal of Guidance, Control, and Dynamics 25, no. 5 (September 2002): 971–74. http://dx.doi.org/10.2514/2.4971.

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Ferrer, Tomás, Sandra Céspedes, and Alex Becerra. "Review and Evaluation of MAC Protocols for Satellite IoT Systems Using Nanosatellites." Sensors 19, no. 8 (April 25, 2019): 1947. http://dx.doi.org/10.3390/s19081947.

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Extending the internet of things (IoT) networks to remote areas under extreme conditions or for serving sometimes unpredictable mobile applications has increased the need for satellite technology to provide effective connectivity. However, existent medium access control (MAC) protocols deployed in commercial satellite networks were not designed to offer scalable solutions for the increasing number of devices predicted for IoT in the near future, nor do they consider other specific IoT characteristics. In particular, CubeSats—a low-cost solution for space technology—have the potential to become a wireless access network for the IoT, if additional requirements, including simplicity and low demands in processing, storage, and energy consumption are incorporated into MAC protocol design for satellite IoT systems. Here we review MAC protocols employed or proposed for satellite systems and evaluate their performance considering the IoT scenario along with the trend of using CubeSats for IoT connectivity. Criteria include channel load, throughput, energy efficiency, and complexity. We have found that Aloha-based protocols and interference cancellation-based protocols stand out on some of the performance metrics. However, the tradeoffs among communications performance, energy consumption, and complexity require improvements in future designs, for which we identify specific challenges and open research areas for MAC protocols deployed with next low-cost nanosatellite IoT systems.
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Pirat, Camille, Finn Ankersen, Roger Walker, and Volker Gass. "$\mathcal{H}_{\infty}$ and $\mu$ -Synthesis for Nanosatellites Rendezvous and Docking." IEEE Transactions on Control Systems Technology 28, no. 3 (May 2020): 1050–57. http://dx.doi.org/10.1109/tcst.2019.2892923.

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Söken, Halil Ersin. "An Attitude Filtering and Magnetometer Calibration Approach for Nanosatellites." International Journal of Aeronautical and Space Sciences 19, no. 1 (March 2018): 164–71. http://dx.doi.org/10.1007/s42405-018-0020-8.

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Belokonov, I. V., I. A. Timbai, and P. N. Nikolaev. "Analysis and Synthesis of Motion of Aerodynamically Stabilized Nanosatellites of the CubeSat Design." Gyroscopy and Navigation 9, no. 4 (October 2018): 287–300. http://dx.doi.org/10.1134/s2075108718040028.

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Yoon, Hyosang, Kathleen M. Riesing, and Kerri Cahoy. "Kalman Filtering for Attitude and Parameter Estimation of Nanosatellites Without Gyroscopes." Journal of Guidance, Control, and Dynamics 40, no. 9 (September 2017): 2272–88. http://dx.doi.org/10.2514/1.g002649.

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Groesbeck, Daniel S., Kenneth A. Hart, and Brian C. Gunter. "Simulated Formation Flight of Nanosatellites Using Differential Drag with High-Fidelity Rarefied Aerodynamics." Journal of Guidance, Control, and Dynamics 42, no. 5 (May 2019): 1175–84. http://dx.doi.org/10.2514/1.g003871.

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Dissertations / Theses on the topic "Nanosatellites – Control systems"

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Lehner, Maximilian Jacob. "Study and design of magnetic attitude control systems for nanosatellites." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2019.

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The objective of this bachelor thesis was to display all the attitude and control systems (ACS) available for CubeSats and how magnetic ACS are the most convenient option in terms of volume. Precisely this project focused on the procedure, the design and the laws of physics that are behind the creation of a torque rod, a magnetic attitude and control system conceived for nanosatellites. After discussing the magnetic laws, the different types of materials of the core, and the geometric parameters of the core and of the wire, all of which determine the operating area of the system, a theoretical model for a torque rod was devised. This was done by using the models present in Niccolò Bellini’s master thesis “Magnetic actuators for nanosatellite attitude control”, 2014. This bachelor thesis ended with the gathering of some experimental data on an embedded magnetorquer collected through a Helmholtz cage.
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Brand, Christiaan Johannes Petrus. "The development of an ARM-based OBC for a nanosatellite." Thesis, Link to the online version, 2007. http://hdl.handle.net/10019.1/2864.

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Mthembu, Sifiso Selby. "An eCos based flight software for a nanosatellite." Thesis, Stellenbosch : University of Stellenbosch, 2009. http://hdl.handle.net/10019.1/1533.

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Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2009.
The nanosatellite is build-up of subsystems and payloads (defined as satellite nodes) connected together into the OBC using CAN bus as the main communication protocol. The flight software application is required to run within the eCos environment on the OBC to monitor and control satellite nodes. The ground station must generate commands and send them to the satellite in space. The application is developed to validate, schedule and dispatch the commands to the satellite nodes at appropriate times. Each node manager, in the flight software, is required to execute the response messages from its respective satellite node. The housekeeping and error recovery data files are defined to convey useful information about satellite status to the user and can be downloaded to the ground station. The flight software is developed using POSIX functions supported by eCos. Although it is not yet ready for real operation in space, the algorithm that can be used for full development is examined and approved.
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Khumalo, Simphiwe. "A CAN based distributed telemetry and telecommand network for a nanosatellite." Thesis, Link to the online version, 2008. http://hdl.handle.net/10019/858.

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Develle, Michael James II. "Optimal attitude control management for a cubesat." Master's thesis, University of Central Florida, 2011. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/4752.

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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.
ID: 030646253; System requirements: World Wide Web browser and PDF reader.; Mode of access: World Wide Web.; Thesis (M.S.A.E.)--University of Central Florida, 2011.; Includes bibliographical references (p. 45-49).
M.S.A.E.
Masters
Mechanical and Aerospace Engineering
Engineering and Computer Science
Aerospace Engineering; Space System Design and Engineering Track
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Erlank, Alexander Olaf. "Development of CubeStar : a CubeSat-compatible star tracker." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/85746.

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Thesis (MEng)-- Stellenbosch University, 2013.
ENGLISH ABSTRACT: The next generation of CubeSats will require accurate attitude knowledge throughout orbit for advanced science payloads and high gain antennas. A star tracker can provide the required performance, but star trackers have traditionally been too large, expensive and power hungry to be included on a CubeSat. The aim of this project is to develop and demonstrate a CubeSat compatible star tracker. Subsystems from two other CubeSat components, CubeSense and CubeComputer, were combined with a sensitive, commercial image sensor and low-light lens to produce one of the smallest star trackers in existence. Algorithms for star detection, matching and attitude determination were investigated and implemented on the embedded system. The resultant star tracker, named CubeStar, can operate fully autonomously, outputting attitude estimates at a rate of 1 Hz. An engineering model was completed and demonstrated an accuracy of better than 0.01 degrees during night sky tests.
AFRIKAANSE OPSOMMING: Die volgende generasie van CubeSats sal akkurate orientasie kennis vereis gedurende 'n volle omwentelling van die aarde. 'n Sterkamera kan die vereiste prestasie verskaf, maar sterkameras is tradisioneel te groot, duur en krag intensief om ingesluit te word aanboord 'n CubeSat. Die doel van hierdie projek is om 'n CubeSat sterkamera te ontwikkel en te demonstreer. Substelsels van twee ander CubeSat komponente, CubeSense en CubeComputer, was gekombineer met 'n sensitiewe kommersiële beeldsensor en 'n lae-lig lens om een van die kleinste sterkameras op die mark te produseer. Algoritmes vir die ster opsporing, identi kasie en orientasie bepaling is ondersoek en geïmplementeer op die ingebedde stelsel. Die gevolglike sterkamera, genaamd CubeStar, kan ten volle outonoom orientasie afskattings lewer teen 'n tempo van 1 Hz. 'n Ingenieursmodel is voltooi en 'n akkuraatheid van beter as 0.01 grade is gedemonstreer.
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Botma, Pieter Johannes. "The design and development of an ADCS OBC for a CubeSat." Thesis, Stellenbosch : Stellenbosch University, 2011. http://hdl.handle.net/10019.1/18040.

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Thesis (MScEng)--Stellenbosch University, 2011.
ENGLISH ABSTRACT: The Electronic Systems Laboratory at Stellenbosch University is currently developing a fully 3-axis controlled Attitude Determination and Control Subsystem (ADCS) for CubeSats. This thesis describes the design and development of an Onboard Computer (OBC) suitable for ADCS application. A separate dedicated OBC for ADCS purposes allows the main CubeSat OBC to focus only on command and data handling, communication and payload management. This thesis describes, in detail the development process of the OBC. Multiple Microcontroller Unit (MCU) architectures were considered before selecting an ARM Cortex-M3 processor due to its performance, power efficiency and functionality. The hardware was designed to be as robust as possible, because radiation tolerant and redundant components could not be included, due to their high cost and the technical constraints of a CubeSat. The software was developed to improve recovery from lockouts or component failures and to enable the operational modes to be configured in real-time or uploaded from the ground station. Ground tests indicated that the OBC can handle radiation-related problems such as latchups and bit-flips. The peak power consumption is around 500 mW and the orbital average is substantially lower. The proposed OBC is therefore not only sufficient in its intended application as an ADCS OBC, but could also stand in as a backup for the main OBC in case of an emergency.
AFRIKAANSE OPSOMMING: Die Elektroniese Stelsels Laboratorium by die Universiteit van Stellenbosch is tans besig om ’n volkome 3-as gestabiliseerde oriëntasiebepaling en -beheerstelsel (Engels: ADCS) vir ’n CubeSat te ontwikkel. Hierdie tesis beskryf die ontwerp en ontwikkeling van ’n aanboordrekenaar (Engels: OBC) wat gebruik kan word in ’n ADCS. ’n Afsonderlike OBC wat aan die ADCS toegewy is, stel die hoof-OBC in staat om te fokus op beheer- en datahantering, kommunikasie en loonvragbestuur. Hierdie tesis beskryf breedvoerig die werkswyse waarvolgens die OBC ontwikkel is. Verskeie mikroverwerkers is as moontlike kandidate ondersoek voor daar op ’n ARM Cortex-M3-gebaseerde mikroverwerker besluit is. Hierdie mikroverwerker is gekies vanweë sy spoed, effektiewe kragverbruik en funksionaliteit. Die hardeware is ontwikkel om so robuust moontlik te wees, omdat stralingbestande en oortollige komponente weens kostebeperkings, asook tegniese beperkings van ’n CubeSat, nie ingesluit kon word nie. Die programmatuur is ontwikkel om van ’n uitsluiting en ’n komponentfout te kan herstel. Verder kan programme wat tydens vlug in werking is, verstel word en vanaf ’n grondstasie gelaai word. Grondtoetse het aangedui dat die OBC stralingverwante probleme, soos ’n vergrendeling (latchup) of bis-omkering (bit-flip), kan hanteer. Die maksimum kragverbruik is ongeveer 500 mW en die gemiddelde wentelbaankragverbruik is beduidend kleiner. Die voorgestelde OBC is dus voldoende as ADCS OBC asook hoof-OBC in geval van nood.
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Groenewald, Christoffel Johannes. "Attitude determination and control system for EyasSAT for Hardware In the Loop application." Thesis, Stellenbosch : Stellenbosch University, 2014. http://hdl.handle.net/10019.1/86653.

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Thesis (MEng) Stellenbosch University, 2014
ENGLISH ABSTRACT: An Attitude Determination and Control System (ADCS) demonstrator and testing platform was required for satellite engineering students. The ADCS demonstrator and testing platform will allow students to develop insight into the concepts and challenges of ADCS design and implementation. The existing model nano-satellite EyasSAT was used as a design platform for a new ADCS demonstrator. A new ADCS module (ADCS_V2) was developed to replace the existing EyasSAT ADCS module. The new module allows for three-axis ADCS and the demonstration of the ADCS on an air bearing platform. The air bearing allows full freedom of movement for yaw rotations with limited pitch and roll rotations. The actuators and sensors required for the ADCS were developed and integrated into EyasSAT. In addition a new PCB was designed to form the ADCS_V2 module. Attitude determination algorithms and attitude control algorithms were implemented and tested using MATLAB Simulink simulations. These algorithms were then implemented on the ADCS_V2 module. The ADCS was tested using Hardware In the Loop (HIL) techniques and an air bearing. The yaw attitude of EyasSAT could be controlled within 0.4 degrees accuracy with all the sensors active. In order to stabilize the air bearing platform, the pitch and roll angles were rate controlled. The pitch and roll rates were damped to within 6 mrad/s.
AFRIKAANSE OPSOMMING: ’n Oriëntasiebepaling en Beheerstelsel (OBBS) demonstrasie en toets platform was benodig vir satellietingenieurswese studente. Die nuwe OBBS sal studente toelaat om insig te ontwikkel met betreking tot die idees en uitdagings wat verband hou met die ontwikkeling en implementering van ’n OBBS. Die huidige nano-sateliet model EyasSAT was gebruik as ’n ontwerpsbasis vir die nuwe OBBS. Die nuwe OBBS was ontwikkel om die huidige module van EyasSAT te vervang. Die nuwe OBBS laat oriëntasiebepaling en -beheer in drie asse toe. Die nuwe OBBS en EyasSAT kan die werking van ’n OBBS demonstreer op ’n luglaerplatform. Die luglaer laat vrye rotasie om die gierhoek toe terwyl die rol- en stygings-as beperk word. Die aktueerders en sensors wat benodig word vir die OBBS is ontwikkel en geïntegreer in EyasSAT saam met ’n nuwe gedrukte stroombaanbord om die nuwe OBBS te vorm. Orientasiebepaling en orientasiebeheer algoritmes is geïmplementeer en getoets met die hulp van MATLAB Simulink simulasies. Die algoritmes was op die OBBS module geïmplementeer en getoets deur gebruik te maak van HIL tegnieke en praktiese toetse op die luglaer. Die rotasie hoek van EyasSAT kan met ’n akkuraatheid van 0.4 grade beheer word indien al die sensors gebruik word. Die rol en stygingshoeksnelheid was gekanselleer om die luglaer stabiel te hou. Die hoeksnelheid van die twee asse kon tot kleiner as 6 mrad/s beheer word.
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Ilutu, Danny Makimi. "Linear power control system for a nanosatellite." Thesis, Cape Peninsula University of Technology, 2011. http://hdl.handle.net/20.500.11838/2202.

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Thesis (MTech(Electrical Engineering))--Cape Peninsula University of Technology, 2011.
Nanosatellite is an electronic device that requires a steady and reliable electrical power supplier (EPS) in order to drive all its electronic circuits. Its unpredictable failures can lead to extensive financial and time losses. The failures may be owing to the environment in which the satellite operates; the technique and the method used to generate power. In order to effectively minimise the risk of the EPS failures, a better technique is essential. The direct energy transfer (DET) technique was chosen for this research because it provides high efficiency and high reliability, unlike the maximum power point tracking (MPPT) technique, which obtains maximum power from the solar cells by using a microcontroller. DET works on a fixed working point of current-voltage characteristic and responds to all satellite power system requirements. The microcontroller is not a suitable device in satellite electrical power systems that requires high reliability, but is used because it is difficult to track the maximum power of solar cells without it. The analog MPPT system is another option, but the technique requires discrete components. Its deployment is limited because of the system's operating frequency and large electronic components such as the inductor and capacitor.
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Schoonwinkel, Johannes. "Attitude determination and control system of a nanosatellite." Thesis, Link to the online version, 2007. http://hdl.handle.net/10019/708.

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Books on the topic "Nanosatellites – Control systems"

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Jeans, Tiger. Design, analysis, testing and implementation of the CanX-1 structural, thermal and attitude control systems. [Downsview, Ont: University of Toronto, Institute for Aerospace Studies], 2003.

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Sarda, Karan. The design, implementation and testing of the thermal control system of the CanX-2 nanosatellite, and, The preliminary design of the attitude determination and control system for the generic nanosatellite bus. 2006.

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Sarda, Karan. The design, implementation and testing of the thermal control system of the CanX-2 nanosatellite & the preliminary design of the attitude determination and control system for the generic nanosatellite bus. 2006.

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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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Eagleson, Stuart. Attitude determination and control: Detailed design, test, and implementation for CanX-2 and preliminary design for CanX-3 and CanX-4/5. 2006.

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Book chapters on the topic "Nanosatellites – Control systems"

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del Castañedo, Ástor, Daniel Calvo, Álvaro Bello, and María Victoria Lapuerta. "Optimization of Fuzzy Attitude Control for Nanosatellites." In Advances in Intelligent Systems and Computing, 970–90. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-030-01057-7_72.

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del Castañedo, Ástor, Álvaro Bello, Karl Olfe, and Victoria Lapuerta. "Effect of the Delay in Fuzzy Attitude Control for Nanosatellites." In Advances in Intelligent Systems and Computing, 966–81. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-29516-5_73.

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Calvo, Daniel, Álvaro Bello, María Victoria Lapuerta, and Ana Laverón-Simavilla. "Comparison of Fuzzy and PID Controllers for the Attitude Control of Nanosatellites." In Advances in Intelligent Systems and Computing, 1062–81. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-030-01057-7_79.

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Lappas, V. J., W. H. Steyn, and C. I. Underwood. "Advanced Micro/Nanosatellite Attitude Control Systems (ACS)." In Smaller Satellites: Bigger Business?, 389–92. Dordrecht: Springer Netherlands, 2002. http://dx.doi.org/10.1007/978-94-017-3008-2_54.

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Bouras, Meryem, Hassan Berbia, and Tamou Nasser. "On Modeling and Fault Tolerance of NanoSatellite Attitude Control System." In Lecture Notes in Electrical Engineering, 409–17. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30301-7_43.

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"MAGNETIC ATTITUDE CONTROL SYSTEMS OF THE NANOSATELLITE TNS-SERIES." In Small Satellites for Earth Observation, 337–44. De Gruyter, 2005. http://dx.doi.org/10.1515/9783110919806.337.

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Conference papers on the topic "Nanosatellites – Control systems"

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Gaber, Khaled, Sayed Nagy, and Amal Zaki. "MEMS gyroscope for attitude propagation and determination for nanosatellites." In 2017 Intl Conf on Advanced Control Circuits Systems (ACCS) Systems & 2017 Intl Conf on New Paradigms in Electronics & Information Technology (PEIT). IEEE, 2017. http://dx.doi.org/10.1109/accs-peit.2017.8303036.

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Belokonov, I. V., I. A. Timbay, and P. N. Nykolaev. "Problems and features of navigation and control of nanosatellites: Experience and lessons learned." In 2017 24th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS). IEEE, 2017. http://dx.doi.org/10.23919/icins.2017.7995670.

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Belokonov, I. V., and M. S. Shcherbakov. "Development of a Single-Axis Control Law Based on SDRE- Technology for Inspection Motion of Two Nanosatellites." In 2021 28th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS). IEEE, 2021. http://dx.doi.org/10.23919/icins43216.2021.9470803.

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Zagorski, P., A. Gallina, J. Rachucki, B. Moczala, S. Zietek, and T. Uhl. "An orbit determination algorithm for small satellites based on the magnitude of the earth magnetic field." In Progress in Flight Dynamics, Guidance, Navigation, and Control – Volume 10, edited by C. Vallet, D. Choukroun, C. Philippe, A. Nebylov, and M. Ganet. Les Ulis, France: EDP Sciences, 2018. http://dx.doi.org/10.1051/eucass/201810035.

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Autonomous attitude determination systems based on simple measurements of vector quantities such as magnetic field and the Sun direction are commonly used in very small satellites. However, those systems always require knowledge of the satellite position. This information can be either propagated from orbital elements periodically uplinked from the ground station or measured onboard by dedicated global positioning system (GPS) receiver. The former solution sacrifices satellite autonomy while the latter requires additional sensors which may represent a significant part of mass, volume, and power budget in case of pico- or nanosatellites. Hence, it is thought that a system for onboard satellite position determination without resorting to GPS receivers would be useful. In this paper, a novel algorithm for determining the satellite orbit semimajor-axis is presented. The methods exploit only the magnitude of the Earth magnetic field recorded onboard by magnetometers. This represents the first step toward an extended algorithm that can determine all orbital elements of the satellite. The method is validated by numerical analysis and real magnetic field measurements.
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Bulut, Murat, Adem Kahriman, and Nedim Sozbir. "Design and Analysis for Thermal Control System of Nanosatellite." In ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-39716.

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It is desirable to be able to turn-around thermal analysis results in a couple of minutes early phases of a satellite thermal design. Therefore, ThermXL-spreadsheet-based Thermal Analysis Tool is one of the very flexible and easy-to-use tool that is suited to preliminary design of a nanosatellite. This paper focuses on the thermal design and the results of an initial analysis of the nanosatellite by using ThermXL. The goal of this study is to take suitable measures to ensure all the components will operate in their safe range of temperatures and also a proper heat rejection. The nanosatellite such as Cube Satellite (CubeSat) is a miniaturized satellite that has dimensions of 10cm × 10cm × 10cm and weights of 1kg. The thermal model of CubeSat was modelled and the thermal analysis was performed. The thermal control analysis on this CubeSat with passive thermal control has been conducted by the ThermXL program that provided by ITP Engines. Temperature distribution of solutions was computed with ThermXL. Temperature data met the need of the mission. The results of the temperatures show that the thermal design of nanosatellite is feasible.
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Cohen, Aaron, Liz Hyde, Darryl Levasseur, Alex Miller, Zack Pirkl, and Periklis Papadopoulos. "Electromagnetic Orientation System for Nanosatellite Navigation." In AIAA Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6646.

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Junquan Li, M. A. Post, and R. Lee. "Nanosatellite attitude air bearing system using variable structure control." In 2012 25th IEEE Canadian Conference on Electrical and Computer Engineering (CCECE). IEEE, 2012. http://dx.doi.org/10.1109/ccece.2012.6334993.

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Choueiri, Marc N., Matthew Bell, and Mason A. Peck. "Cost-Effective and Readily Manufactured Attitude Determination and Control System for NanoSatellites." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0802.

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Li, Junquan, Mark Post, and Regina Li. "Real Time Fault Tolerant Nonlinear Attitude Control System for Nanosatellite Applications." In Infotech@Aerospace 2012. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-2428.

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Li, Junquan, Mark A. Post, and Regina Lee. "A novel adaptive unscented Kalman filter attitude estimation and control systems for 3U nanosatellite." In 2013 European Control Conference (ECC). IEEE, 2013. http://dx.doi.org/10.23919/ecc.2013.6669761.

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