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Journal articles on the topic 'Picosatellite'

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Author: Grafiati

Published: 4 June 2021

Last updated: 7 February 2022

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1

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, and 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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2

LaBerteaux, Jason, Jason Moesta, and Blaise Bernard. "Advanced Picosatellite Experiment." IEEE Aerospace and Electronic Systems Magazine 24, no. 9 (September 2009): 4–9. http://dx.doi.org/10.1109/maes.2009.5282283.

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3

Vertat, Ivo, and 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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4

Céspedes, Jorge Enrique Salamanca, and Roberto Ferro Escobar. "Diseño e Implementacion de un Modulo de Gestion de Energia para un Pico-Satelite Tipo Cubesat." KnE Engineering 3, no. 1 (February 11, 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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5

Wermuth, Martin, Gabriella Gaias, and Simone D’Amico. "Safe Picosatellite Release from a Small Satellite Carrier." Journal of Spacecraft and Rockets 52, no. 5 (September 2015): 1338–47. http://dx.doi.org/10.2514/1.a33036.

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6

Scholz, A., W. Ley, B. Dachwald, J. J. Miau, and J. C. Juang. "Flight results of the COMPASS-1 picosatellite mission." Acta Astronautica 67, no. 9-10 (November 2010): 1289–98. http://dx.doi.org/10.1016/j.actaastro.2010.06.040.

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7

Yao, J. Jason, Charles Chien, Robert Mihailovich, Viktor Panov, Jeffrey DeNatale, Judy Studer, Xiaobin Li, Anhua Wang, and Sangtae Park. "Microelectromechanical system radio frequency switches in a picosatellite mission." Smart Materials and Structures 10, no. 6 (November 28, 2001): 1196–203. http://dx.doi.org/10.1088/0964-1726/10/6/308.

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8

Arnon, Shlomi, and Debbie Kedar. "Sensing and communication trade-offs in picosatellite formation flying missions." Journal of the Optical Society of America A 26, no. 10 (September 3, 2009): 2128. http://dx.doi.org/10.1364/josaa.26.002128.

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9

Fadlie Sabri, Sharizal, Nor'Asnilawati Salleh, and Elena Woo Lai Leng. "Designing and Developing a Ground Operation Software for Picosatellite Operation and Data Processing." Applied Mechanics and Materials 225 (November 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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10

Reichel, F., P. Bangert, S. Busch, K. Ravandoor, and K. Schilling. "The Attitude Determination and Control System of the Picosatellite UWE-3*." IFAC Proceedings Volumes 46, no. 19 (2013): 271–76. http://dx.doi.org/10.3182/20130902-5-de-2040.00088.

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11

Mattos, Everson, Antonio M. S. S. Andrade, Guilherme V. Hollweg, Mario L. da S. Martins, and Jose R. Pinheiro. "Analysis and design of a stacked power subsystem on a picosatellite." IEEE Aerospace and Electronic Systems Magazine 33, no. 10 (October 2018): 4–13. http://dx.doi.org/10.1109/maes.2018.170076.

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12

Soken, Halil Ersin, and Chingiz Hajiyev. "Adaptive Fading UKF with Q-Adaptation: Application to Picosatellite Attitude Estimation." Journal of Aerospace Engineering 26, no. 3 (July 2013): 628–36. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000178.

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13

Jayaram, Sanjay, Mark McQuilling, and Sridhar Condoor. "PRO/MECHANICA-based structural and random vibration analysis of picosatellite structure." International Journal of Computer Aided Engineering and Technology 4, no. 1 (2012): 90. http://dx.doi.org/10.1504/ijcaet.2012.044585.

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14

Jayaram, Sanjay. "Design and analysis of nano momentum wheel for picosatellite attitude control system." Aircraft Engineering and Aerospace Technology 81, no. 5 (September 4, 2009): 424–31. http://dx.doi.org/10.1108/00022660910983707.

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15

Qiao, Qiao, Jianping Yuan, Mingming Wang, and Xin Ning. "Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation." Aerospace Science and Technology 71 (December 2017): 62–67. http://dx.doi.org/10.1016/j.ast.2017.09.011.

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16

Busch, Stephan, and Klaus Schilling. "Robust and Efficient OBDH Core Module for the Flexible Picosatellite Bus UWE-3." IFAC Proceedings Volumes 46, no. 19 (2013): 218–23. http://dx.doi.org/10.3182/20130902-5-de-2040.00107.

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17

Jayaram, Sanjay. "Design of template to fabricate magnetic torquer coils for nano and picosatellite missions." Journal of Engineering, Design and Technology 8, no. 2 (July 13, 2010): 158–67. http://dx.doi.org/10.1108/17260531011062537.

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18

Moon, Byoung-Young, Young-Hyun Kim, and Young-Keun Chang. "Development of HAUSAT-1 Picosatellite Communication Subsystem as a Test Bed for Small Satellite Technology." International Journal of Aeronautical and Space Sciences 5, no. 1 (June 30, 2004): 6–18. http://dx.doi.org/10.5139/ijass.2004.5.1.006.

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19

Guennoun, Zouhair, Adnane ADDAIM, and Abdelhaq Kherras. "Enhanced MAC protocol for designing a Wireless Sensor Network based on a single LEO Picosatellite." International Journal of Sensor Networks 1, no. 1 (2015): 1. http://dx.doi.org/10.1504/ijsnet.2015.10001250.

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20

Addaim, Adnane, Abdelhaq Kherras, and Zouhair Guennoun. "Enhanced MAC protocol for designing a wireless sensor network based on a single LEO Picosatellite." International Journal of Sensor Networks 23, no. 3 (2017): 143. http://dx.doi.org/10.1504/ijsnet.2017.083399.

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21

Kataoka, J., T. Toizumi, T. Nakamori, Y. Yatsu, Y. Tsubuku, Y. Kuramoto, T. Enomoto, et al. "In-orbit performance of avalanche photodiode as radiation detector on board the picosatellite Cute-1.7+APD II." Journal of Geophysical Research: Space Physics 115, A5 (May 2010): n/a. http://dx.doi.org/10.1029/2009ja014699.

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22

Yang, Bo, Jun Miao, Zichen Fan, Jun Long, and Xuhui Liu. "Allocation Optimization Strategy for High-Precision Control of Picosatellites and Nanosatellites." International Journal of Aerospace Engineering 2018 (July 15, 2018): 1–15. http://dx.doi.org/10.1155/2018/6239725.

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The high-precision control of picosatellites and nanosatellites has always plagued the astronautics field. Aiming to change the status quo of the actuators not being able to meet the high-precision attitude control of picosatellites and nanosatellites, this article formulates a control allocation strategy for picosatellites and nanosatellites using the solid propellant microthruster array (SPMA). To solve the problem of the diversity and complexity of ignition combinations brought about by the high integration of the SPMA, the energy consumption factor of the optimal allocation is established, and the relationships of the array’s energy consumption factor, the control accuracy, the number, and the ignition combinations of the thruster array are deduced. The optimization objective is introduced by Sherman-Morrison formula and singular value decomposition. Thus, the energy consumption problem is transformed into an integer programming problem, acquiring the control allocation strategy and the optimal thruster energy. Simulation results show that the proposed algorithm can effectively reduce the thrust energy consumption and improve the precision control, demonstrating the feasibility and efficiency of the proposed algorithm for picosatellites and nanosatellites.

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23

Rodríguez, Juan Sebastián, Andrés Yarce Botero, Diego Valle, Julián Gálvez Serna, and Francisco Botero. "Experimental Approach for the Evaluation of the Performance of a Satellite Module in the CanSat Form Factor for In Situ Monitoring and Remote Sensing Applications." International Journal of Aerospace Engineering 2021 (April 17, 2021): 1–28. http://dx.doi.org/10.1155/2021/8868797.

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This article includes the phases of conceptualization and validation of a picosatellite prototype named Simple-2 for remote sensing activities using COTS (Commercial-Off-The-Shelf) components and the modular design methodology. To evaluate its performance and ensure the precision and accuracy of the measurements made by the satellite prototype, a methodology was designed and implemented for the characterization and qualification of CanSats (soda can satellites) through statistical tests and techniques of DoE (Design of Experiments) based on CubeSat aerospace standards and regulations, in the absence of official test procedures for these kinds of satellite form factor. For the above, two experimental units were used, and all the performance variables of the different satellite subsystems were discriminated. For the above, two experimental units were used, and all the performance variables of the different satellite subsystems were discriminated against. These were grouped according to the dependence of the treatments formulated in thermal and dynamic variables. For the tests of the first variables, a one-factor design was established using dependent samples on each of the treatments. Then, hypothesis tests were performed for equality of medians, using nonparametric analysis of the Kruskal-Wallis variance. Additionally, multivariate analysis of variance was carried out for nonparametric samples (nonparametric multivariate tests), and the application of post hoc multiple-range tests to identify the treatments that presented significant differences within a margin of acceptability. To know the dynamic response and ensure the structural integrity of the satellite module, shock, oscillation, and sinusoidal tests were applied through a shaker. Having applied the experimental methodology to the different units, the results of a real experiment are illustrated in which a high-altitude balloon was used through the application of nonparametric regression methods. This experiment’s interest measured thermodynamic variables and the concentration of pollutants in the stratosphere to corroborate the operating ranges planned in the above experiments using on-flight conditions and estimate the TLR (technology readiness level) of future prototypes.

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24

Mantzouris, Georgios, Periklis Papadopoulos, Nikitas Nikitakos, Marco Manso, Alexander Bordetsky, Zacharias Sarris, Garik Markarian, and Kyriakos I. Kourousis. "Picosatellites for Maritime Security Applications - the Lambdasat Case." Journal of Aerospace Technology and Management 7, no. 4 (December 2, 2015): 490–503. http://dx.doi.org/10.5028/jatm.v7i4.551.

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25

Bell, Iverson C., Brian E. Gilchrist, Jesse K. McTernan, and Sven G. Bilén. "Investigating Miniaturized Electrodynamic Tethers for Picosatellites and Femtosatellites." Journal of Spacecraft and Rockets 54, no. 1 (January 2017): 55–66. http://dx.doi.org/10.2514/1.a33629.

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26

Nebylov, A. V., A. E. Medina Padron, and Sukrit Sharan. "Relative Motion Control of PicoSatellites Constellation in Independent Orbits." IFAC-PapersOnLine 49, no. 17 (2016): 355–60. http://dx.doi.org/10.1016/j.ifacol.2016.09.061.

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27

Kronhaus, Igal, Klaus Schilling, Mathias Pietzka, and Jochen Schein. "Simple Orbit and Attitude Control Using Vacuum Arc Thrusters for Picosatellites." Journal of Spacecraft and Rockets 51, no. 6 (November 2014): 2008–15. http://dx.doi.org/10.2514/1.a32796.

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28

Li, Yuepei, Symon K. Podilchak, Dimitris E. Anagnostou, Constantin Constantinides, and Tom Walkinshaw. "Compact Antenna for Picosatellites Using a Meandered Folded-Shorted Patch Array." IEEE Antennas and Wireless Propagation Letters 19, no. 3 (March 2020): 477–81. http://dx.doi.org/10.1109/lawp.2020.2966088.

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29

Kéchichian, Jean A., Eric T. Campbell, Michael F. Werner, and Ernest Y. Robinson. "Solar surveillance zone population strategies with picosatellites using halo and distant retrograde orbits." Acta Astronautica 56, no. 5 (March 2005): 495–506. http://dx.doi.org/10.1016/j.actaastro.2004.10.003.

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30

Wang, Wenlong, Xiaotian Zhang, Daqian Hao, and Wenfei Gong. "Design and analysis of an integrated device for launch adapter and resettable orbital deployer for picosatellites." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 3 (December 11, 2019): 818–26. http://dx.doi.org/10.1177/0954410019890744.

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The design, analysis, and test of the integrated device for the launch adapter and the resettable orbital deployer are presented in this paper. This integrated device contains both functions of the single-use launch adapter and the resettable orbital deployer. Two types of release mechanisms are combined. The four-bar linkage mechanism is applied in the single-use adapter function. This release mechanism provides sufficient strength of connection in the launch stage and is released when entering the orbit. The electromagnetic hook mechanism is applied in the resettable orbital deployer. The deployer can be reloaded by the manipulator on the mother satellite with picosatellites taken out from the cargo to deploy multiple times. Dynamics simulation, finite element simulation, as well as the prototype test verify the preliminary feasibility of this design.

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31

Tang, Jie, Mao Jun Fan, and Jun Hu. "Research on the Gerschgorin Radii Estimator Based on Real-Valued Decomposition Technique in Picosatellites." Applied Mechanics and Materials 529 (June 2014): 600–604. http://dx.doi.org/10.4028/www.scientific.net/amm.529.600.

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In order to reduce the computational burden, real-valued decomposition technique is applied in picosat positioning. Through converting the correlation matrix to real-valued matrix, the real-valued decomposition technique not only reduces the computer burden of matrix decomposition, but also makes the correlation matrix more close to Toeplitz matrix through a forward-backward smoothing. Simulations confirm that the real-valued Gerschgorin Radii shows an improved performance.

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32

Hamrouni, Chafaa, Rached Hamza, Bilel Neji, Alim R. Aslan, Hiroshi Nakajima, and Adel M. Alimi. "PETRI-NET MODELING AND PROTOTYPE OF A MULTIMICROSTRIP ANTENNAE NETWORK FUZZY CONTROLLED SYSTEM FOR PICOSATELLITES." Applied Artificial Intelligence 27, no. 10 (November 26, 2013): 881–912. http://dx.doi.org/10.1080/08839514.2013.823325.

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33

Kamei, Tomoki, Makoto Matsui, and Koichi Mori. "Feasibility study of a laser launch system for picosatellites and nanosatellites in low-earth orbits." Acta Astronautica 176 (November 2020): 124–30. http://dx.doi.org/10.1016/j.actaastro.2020.06.014.

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34

Gopal, Banala Krishna. "Atmospheric Data Collecting Cubesat using Raspberry PI." International Journal for Research in Applied Science and Engineering Technology 9, no. VI (June 30, 2021): 3880–88. http://dx.doi.org/10.22214/ijraset.2021.35848.

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As advances in technology make payloads and instruments for space missions smaller, lighter, and more power efficient, a distinct segment market is emerging for low-cost missions on very small spacecrafts such as - micro, nano, and picosatellites. Due to the fact that even after many technological advances the usage of miniature satellites the remote sensing of atmospheric is still not a widely explored aspect, to overcome this we idealized a system to build a CUBESAT which can be built with minimal efforts. We proposed this system with an objective to build a CUBESAT to detect different weather aspects of our earth at the troposphere layer which is the lowest layer of earth. We implemented our project using the Raspberry Pi due to its versatility in multi-processing and connectivity. Here the Raspberry-Pi is going to be configured with transceiver modules in the CUBESAT’s sender-end to gather atmospheric data associated with temperature, gasses present, humidity and pressure using CUBESAT sensors and after the reception of data at ground station by Arduino configured as receiver, data is going to be stored in an accessible website for viewing and further computations.

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35

Zakšek, Klemen, Mike R. James, Matthias Hort, Tiago Nogueira, and Klaus Schilling. "Using picosatellites for 4-D imaging of volcanic clouds: Proof of concept using ISS photography of the 2009 Sarychev Peak eruption." Remote Sensing of Environment 210 (June 2018): 519–30. http://dx.doi.org/10.1016/j.rse.2018.02.061.

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36

Лапханов, Эрик Александрович, and Александр Сергеевич Палий. "СОВРЕМЕННЫЕ ЗАДАЧИ СОЗДАНИЯ И УВОДА С ОРБИТЫ ГРУППИРОВОК КОСМИЧЕСКИХ АППАРАТОВ КЛАССА НАНО И ПИКО." Aerospace technic and technology, no. 4 (October 14, 2018): 20–35. http://dx.doi.org/10.32620/aktt.2018.4.03.

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The purpose of the present paper is the analysis of current tasks concerning with creation and deorbiting of the formation flying groups consist of nano- and picosatellites and the consideration of the possibility of using permanent magnet devices for the deorbiting of these groups. During research was determined that it is most expedient to use small standardized spacecraft and use them during the development of distributed satellite systems. It can be both formations, and groups of satellites spaced a long distance. The analysis of the current possibilities for the removal of nano- and pico- spacecraft into orbit is carried out. According to the characteristics and properties of super-small spacecraft because of their super-small size and saving of the rocket fuel, it was determined that these spacecrafts proposed to be launch as a passing payload when large, expensive spacecraft is launched into orbit. To facilitate the integration of spacecrafts such as CubeSats with a carrier rocket, special multi-purpose dispensers were developed. The problems of controlling the configuration of the nano- and pico- satellites formations are shown. The analysis of deorbiting technologies of spacecrafts of the nano- and pico- satellites is carried out. The overview of modern well-known propulsion technologies of nano- and pico- satellites is carried out. The new method of creation and deorbiting of the formation flying groups from nano- and pico- satellites with using new constructive scheme “spherical dispensers” was proposed. The main axes of P-PODs are located along the radiuses of “spherical dispenser”. The technology of deploying and “clotting “of the formation flying groups from nano- and pico- satellites with using tether connection and hoist devices was proposed. The analysis of the possibility of implementation of devices with permanent magnets for nano- and pico- satellites is carried out. The low boundaries of effective work of the magnetic devices were determined. An alternative method for deorbiting nano- and pico- spacecrafts with the help of devices with permanent magnets using “clotting “technology is proposed

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37

Aksiutenko, A. M., Yu P. Yefymov, R. A. Kantserova, M. V. Petrushenko, and T. H. Smila. "Experimental system for studying the effect of the arrangement of nonhermetic module fillers on the outgassing flow density." Technical mechanics 2020, no. 4 (December 10, 2020): 82–96. http://dx.doi.org/10.15407/itm2020.04.082.

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In recent years, components and materials of industrial and commercial quality have been in frequent use in the assembly of small spacecraft to reduce the cost of space projects. This may affect spacecraft and onboard equipment reliability and performance quality. In particular, a high risk may arise from unpredictable performance characteristics of components and materials of this type caused by outgassing flows of unregulated density. The situation is aggravated by difficulties in numerical simulation of the complex internal geometry of actual nonhermetic small spacecraft. The most efficient way to resolve this problem is to conduct laboratory tests. This paper presents an experimental system for studying the dependence of degassing processes on the geometry of arrangement of electronics boards and various structural materials in a nonhermetic module. The theoretic basis for experiments is a differential realization of the accumulation method, which allows one to differentiate the density of degassing flows from particularly arranged specimens and elements of the module’s inner surface. To reproduce the design features of nonhermetic nano- and picosatellites, models of nonhermetic modules were refined, and a special laboratory module was made on their basis. For this purpose, a unit of synchronous module evacuation control was updated, equipment was developed for positioning plate-type fillers of nonhermetic modules, the recording of gas-dynamic parameters of a nonhermetic module’s own internal atmosphere was provided, and an automated experiment control system was prepared. The laboratory module was integrated into the automated measuring system of the VAU-2M vacuum aerodynamic installation of the Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine. The experimental system developed was tested to show a satisfactory operability of both its components and the system as a whole. The system developed allows one to study outgassing from the surface of various components and materials, to measure the density of outgassing flows for various equipment arrangements, and to study the dynamics of outflow of the products of the own internal atmosphere through calibrated orifices, which simulate the outflow of the own internal atmosphere of a nonhermetic module through its unregulated clearances.

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38

"Developing Picosatellite Flight Software." American Journal of Science & Engineering 1, no. 1 (2019). http://dx.doi.org/10.15864/ajse.1104.

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39

Bokade, Rohit, Supriya Bhide, Harsh Namdeo Bhor, Nisha Vanjari, and Umesh Shinde. "Development of an Arduino based PicoSatellite-OBC." SSRN Electronic Journal, 2020. http://dx.doi.org/10.2139/ssrn.3561174.

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40

"Mechanical System Design and Development of the HAUSAT-1 Picosatellite." Journal of the Korean Society for Aeronautical & Space Sciences 32, no. 9 (November 1, 2004): 103–13. http://dx.doi.org/10.5139/jksas.2004.32.9.103.

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41

"Development of Low-Cost and Low-Power Picosatellite Electrical Power Subsystem." Journal of the Korean Society for Aeronautical & Space Sciences 32, no. 7 (September 1, 2004): 105–16. http://dx.doi.org/10.5139/jksas.2004.32.7.105.

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42

Qiao, Qiao, Jianping Yuan, Yong Shi, Xin Ning, and Fei Wang. "Structure, Design, and Modeling of an Origami-Inspired Pneumatic Solar Tracking System for the NPU-Phonesat." Journal of Mechanisms and Robotics 9, no. 1 (December 2, 2016). http://dx.doi.org/10.1115/1.4035086.

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Various plants have the ability to follow the sun with their flowers or leaves via a mechanism known as heliotropism, which is powered by pressure gradients between neighboring motor cells. Adapting this bio-inspired mechanism, in this paper we present a novel origami-inspired pneumatic solar tracking system for a picosatellite named NPU-PhoneSat that is capable of solar tracking without altering the attitude of the NPU-PhoneSat. We give an overview of the system design and address the theoretical problem of modeling the origami-inspired pneumatic solar tracking system. The theoretical results are compared with the experimental data, demonstrating the validity of the proposed analytical model. Such understanding of soft solar trackers will allow their performance to be predicted, thus enabling their wide utilization in enhancing energy supply.

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A, Ampatzoglou, Baltopoulos A, Kotzakolios A, and Kostopoulos V. "Qualification of Composite Structure for Cubesat Picosatellites as a Demonstration for Small Satellite Elements." International Journal of Aeronautical Science & Aerospace Research, September 2, 2014, 1–10. http://dx.doi.org/10.19070/2470-4415-140001.

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Guerrieri, Daduí C., Angelo Cervone, and Eberhard Gill. "Analysis of Nonisothermal Rarefied Gas Flow in Diverging Microchannels for Low-Pressure Microresistojets." Journal of Heat Transfer 138, no. 11 (July 19, 2016). http://dx.doi.org/10.1115/1.4033955.

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Heat transfer and fluid flow through different microchannel geometries in the transitional regime (rarefied flow) are analyzed by means of direct simulation Monte Carlo (DSMC) simulations. Four types of three-dimensional microchannels, intended to be used as expansion slots in microresistojet concepts, are investigated using nitrogen as working fluid. The main purpose is to understand the impact of the channel geometry on the exit velocity and the transmission coefficient, parameters which are well known to affect directly the thruster performance. Although this analysis can be applied in principle to several possible microfluidics scenarios, particular focus is given to its application in the field of space propulsion for micro-, nano-, and picosatellites, for which the requirements ask for low thrust levels from some micronewtons to a few millinewtons and moderate specific impulse, as well as a low power consumption in the order of a few watts. Analysis shows that the thrust produced by one single microchannel can be increased by about 480% with a careful selection of the channel geometry, decreasing at the same time the specific impulse by just 5%, with a power consumption decrease of more than 66.7%.

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Espíndola Díaz, Jorge Enrique, and Jairo Alonso Mesa Lara. "Implementación de estación terrena para seguimiento a picosatélites de órbita LEO [Implementation of ground station for tracking LEO orbit picosatellites]." Ventana Informatica, no. 26 (June 20, 2012). http://dx.doi.org/10.30554/ventanainform.26.137.2012.

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Resumen El presente artículo muestra los resultados de una investigación acerca de estaciones terrenas de seguimientos a picosatélites, que se desarrolla en la Universidad Pedagógica y Tecnológica de Colombia. Presenta el marco referencial, la metodología y los resultados de dicha investigación. El objetivo principal consiste en plantear un diseño de la estación que cumpla con los lineamientos y normativas que a nivel de radiocomunicaciones se imponen y que sea escalable en cuanto permita que a futuro la estación terrena satelital de la Universidad se logre integrar a la red de estaciones mundiales. Se concluye con el diseño de las comunicaciones para la estación y con una serie de recomendaciones para la posterior fase de implementación. Palabras claveEstación terrena, picosatélites, radioenlace Abstract This paper presents the results of an investigation of ground stations to pico-tracking, which takes place at the Pedagogical University and Technology of Colombia by the group INFELCOM. It presents the frame of reference, methodology and results of such research. The main objective is to raise a station design that meets the guidelines and regulations that are imposed at radio and are scalable in the future allow the satellite earth station of the university can integrate the network of stations worldwide. It concludes with the design of communications for the season and a series of recommendations for the subsequent implementation phase.KeywordsEarth station, picosatellites, radio link

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