A Low-Cost Attitude Determination and Control System for the UYS-1 nanosatellite

Oliveira, Gabriel Frenchiani de; Ishihara, J.Y.; Borges, Renato Alves; Ferreira, Henrique C.; Kulabukhov, Anatolyi M.; Larin, Vladimir A.; Belikov, Vladimir V.

doi:10.1109/aero.2013.6496982

Cited by 9 publications

(8 citation statements)

References 32 publications

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“…As in many other projects, the preferred angular kinematics attitude representation is in quaternions [8], [9], [10]. This is justified by the absence of singularities and the fact that they provide a convenient product rule for successive rotations, which makes them computationally faster than other representations (see [3] for more information).…”

Section: Description Of the Antelsat Cubesatmentioning

confidence: 99%

An inexpensive Attitude Determination system for the Uruguayan Cubesat, AntelSat

Tassano¹,

Monzón²,

Ramos³

et al. 2014

2014 IEEE International Instrumentation and Measurement Technology Conference (I2MTC) Proceedings

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This paper discusses the design and development of an Attitude Determination and Control System (ADCS) for the first Uruguayan nanosatellite, AntelSat, which is being built at UdelaR University in Uruguay. The satellite consists of a twounit (2U) Cubesat, which implies that the ADCS is designed under tight mass, size and energy constraints. For the attitude determination section, data available from sensors is taken as inputs for the computation of an optimal quaternion estimator. The use of an unscented Kalman filter is also discussed. The selection of hardware and algorithms is addressed. Though observing the system requirements and restrictions, the results display that it is possible to attain reasonable attitude estimation without the need for expensive sensor setups.

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Section: Description Of the Antelsat Cubesatmentioning

confidence: 99%

An inexpensive Attitude Determination system for the Uruguayan Cubesat, AntelSat

Tassano¹,

Monzón²,

Ramos³

et al. 2014

2014 IEEE International Instrumentation and Measurement Technology Conference (I2MTC) Proceedings

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“…As such, SERPENS 1 was the result of a multinational effort involving Brazil, Spain, Italy, and the USA. Nationally, several universities and institutions took part in SERPENS 1 (such as INPE; Fernandes et al 2016), under the coordination of the University of Brasília (Figueiró 2014;de Oliveira et al 2015;Gonçalves and Veras 2016), with over 100 students involved.…”

Section: Case Study: Serpens 1 Missionmentioning

confidence: 99%

“…In view of the previous knowledge used to build SERPENS 1 (Figueiró 2014;de Oliveira et al 2015;Gonçalves and Veras 2016), the following information is relevant to the PBS creation:…”

Section: Appendix: Compiling the Output Report Of Serpensmentioning

confidence: 99%

AEB Online Calculator for Assessing Technology Maturity: IMATEC

Xavier¹,

Veloso²,

Souza³

et al. 2020

J.Aerosp. Technol. Manag.

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This paper exposes initially the motivations for developing a TRL online calculator by AEB (Brazilian Space Agency; in Portuguese, Agência Espacial Brasileira). Such motivations demand the tool to be a way not only to assess the TRL condition of operational space missions and systems, but also as a method of evaluating and sharing proposals with new technological content. The TRL methodology and its relation to risk management are discussed. The development phases of the IMATEC Lite application are then described, with emphasis to the data handling structure capable of storing the user product model. A result of technology assessment using the software is detailed by presenting the PBS of the SERPENS 1 mission nanosatellite. The prospects of using the tool for judging the acceptability of new missions and projects are discussed, as well as some of the encountered difficulties.

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“…Kentucky Space is an example of a consortium, led by Kentucky University, responsible for satellites KySat‐1 and KySat‐2 10‐12 . More recently, SERPENS consortium, an international collaboration of universities, lead by the Brasilia University (UnB), launched the 3U CubeSat SERPENS‐I 13,14 . The SERPENS program is still active, with the ongoing development of SERPENS‐II nanosatellite, now lead by the Federal University of Santa Catarina (UFSC).…”

Section: Introductionmentioning

confidence: 99%

Nanosatellite electrical power system architectures: Models, simulations, and tests

Slongo

Martinez

Eiterer

et al. 2020

Circuit Theory & Apps

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KESSLER SLONGO ET AL. power point tracking (MPPT) techniques, high-efficiency solar cells, and energy-aware scheduling algorithms are some of the hot topics under research nowadays. Due to size restrictions and aiming low complexity in design, many nanosatellite designers adopt the direct energy transfer (DET) architecture. KySat-2 is an example of a successfully accomplished mission, based on this EPS topology. Designed by Morehead State University Space Science and Engineering group, KySat-2 EPS was powered by a set of gold-plated deployable solar panels with 26% of efficiency. It provided four high-power regulated rails (two 3.3 V and two 5 V) and a low-noise, low power 3.3V rail for noise-sensitive devices. The energy storage system was made of three 18650 lithium-ion cells connected in series, and the high-power rails reached efficiencies approaching 90%. 12,21 Aiming minimum space occupation and low power consumption, the EPS proposed for the AraMiS project has a boost regulator operating the solar panels close to their MPP. 16 In order to reduce the number of components, the designers opted by the constant voltage MPPT algorithm, using only analog devices. The EPS steps up solar panels voltage from 4.4 V to the distribution bus voltage level (14 ± 2 V). It provides power buses with 3.3 and 5 V voltage levels. The EPS efficiency analysis is demonstrated, calculating the main components power losses. Although this is a very detailed and well-described work, it does not compare the proposed solution with other EPS architectures. A 3U EPS efficiency analysis is presented by Gonzalez-Llorente et al. 22 The subsystem is based on a buck converter that steps down the solar panels voltage (15 or 7.5 V) to the litChium-ion battery range of 3.3 or 6.6 V. The authors define an optimum operation point for the DC-DC converter in order to achieve its maximum efficiency. The operation point is defined by the converter input voltage, output voltage, and output power. Therefore, the discussion is based on different solar cells connections configurations, and battery cells arrangement, that result in the most efficient EPS configuration. Different scenarios have been analyzed to achieve 98% of peak efficiency on the best configuration: input voltage of 7.4 V, output voltage of 3.3 V, and output current varying from 0.1 mA to 2.1 A. Only the buck converter topology is discussed in this paper, and it does not consider any MPPT technique. An interesting solution adopted for the ERPSAT-1 picosatellite uses fuzzy logic to obtain energy harvesting maximization. 23 The developed subsystem has three main blocks, which are the fuzzy maximum power point tracker, the power conditioner, and the hierarchical fuzzy subsystem controller. The fuzzy logic algorithm has been implemented in a dedicated microcontroller that controls a boost converter. Simulations have been performed to demonstrate the better efficiency of the proposed method when compared to the Perturb and Observe MPPT algorithm. Although a comparison is provided in this work,...

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A Low-Cost Attitude Determination and Control System for the UYS-1 nanosatellite

Cited by 9 publications

References 32 publications

An inexpensive Attitude Determination system for the Uruguayan Cubesat, AntelSat

An inexpensive Attitude Determination system for the Uruguayan Cubesat, AntelSat

AEB Online Calculator for Assessing Technology Maturity: IMATEC

Nanosatellite electrical power system architectures: Models, simulations, and tests

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