Journal articles: 'Small Satellite Propulsion'

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Lotfy, A., W. Anis, and Joseph V. M. Halim. "Design PV system for a small GEO satellite and studying the effect of using different types of propulsion." International Journal of Advances in Applied Sciences 8, no. 1 (March 1, 2019): 54. http://dx.doi.org/10.11591/ijaas.v8.i1.pp54-63.

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<p>This paper presents an optimum design of the solar Photo-Voltaic (PV) power system for small Geostationary Earth Orbit (GEO) satellites using triple junction solar cells and advanced Lithium Ion batteries. The paper applies the proposed system on various propulsion technologies; full chemical, full electrical and hybrid propulsions. This research work studies the capability to fulfil efficiently all the satellite power requirements during both the launching and the on-station phases while reducing the high cost challenge. Since the propulsion type is a key factor for the satellite cost, an economic analysis is demonstrated and investigated in two different strategies. The first scenario fixes the satellite weight and offers the revenue due to the increase in the satellite payload. However, the second scenario evaluates the saving profits due to the reduction in the satellite weight using the same number of satellite transponders. The analytical comparison among the different propulsion techniques shows the superior advantages of using the full electrical satellites. </p>

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Sochacki, Mateusz, and Janusz Narkiewicz. "Propulsion System Modelling for Multi-Satellite Missions Performed by Nanosatellites." Transactions on Aerospace Research 2018, no. 4 (December 1, 2018): 58–67. http://dx.doi.org/10.2478/tar-2018-0030.

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Abstract Progress in miniaturization of satellite components allows complex missions to be performed by small spacecraft. Growing interest in the small satellite sector has led to development of standards such as CubeSat, contributing to lower costs of satellite development and increasing their service competitiveness. Small satellites are seen now as a prospective replacement for conventional sized satellites in the future, providing also services for demanding users. New paradigms of multi-satellite missions such as fractionation and federalization also open up new prospects for applications of small platforms. To perform a comprehensive simulation and analysis of future nanosatellite missions, an adequate propulsion system model must be used. Such model should account for propulsion solutions which can be implemented on nanosatellites and used in multi-satellite missions. In the paper, concepts of distributed satellite systems (constellations, formations, fractionated and federated) are described with a survey of past, on-going and planned multi-satellite nanosatellites missions. Currently developed propulsion systems are discussed and the models of propulsion systems embedded in the WUT satellite simulation model are presented.

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Potrivitu, George-Cristian, Yufei Sun, Muhammad Wisnuh Aggriawan bin Rohaizat, Oleksii Cherkun, Luxiang Xu, Shiyong Huang, and Shuyan Xu. "A Review of Low-Power Electric Propulsion Research at the Space Propulsion Centre Singapore." Aerospace 7, no. 6 (May 28, 2020): 67. http://dx.doi.org/10.3390/aerospace7060067.

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The age of space electric propulsion arrived and found the space exploration endeavors at a paradigm shift in the context of new space. Mega-constellations of small satellites on low-Earth orbit (LEO) are proposed by many emerging commercial actors. Naturally, the boom in the small satellite market drives the necessity of propulsion systems that are both power and fuel efficient and accommodate small form-factors. Most of the existing electric propulsion technologies have reached the maturity level and can be the prime choices to enable mission versatility for small satellite platforms in Earth orbit and beyond. At the Plasma Sources and Applications Centre/Space Propulsion Centre (PSAC/SPC) Singapore, a continuous effort was dedicated to the development of low-power electric propulsion systems that can meet the small satellites market requirements. This review presents the recent progress in the field of electric propulsion at PSAC/SPC Singapore, from Hall thrusters and thermionic cathodes research to more ambitious devices such as the rotamak-like plasma thruster. On top of that, a review of the existing vacuum facilities and plasma diagnostics used for electric propulsion testing and characterization is included in the present research.

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Khandekar, Pravin, Kanishka Biswas, Dushyant Kothari, and H. Muthurajan. "Nano Mechanical Properties of Ceramic Polymer Composite Micro Thruster Developed Using 3D Printing Technology." Advanced Science Letters 24, no. 8 (August 1, 2018): 5884–90. http://dx.doi.org/10.1166/asl.2018.12214.

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Nano and micro satellites, when revolving around the earth, may drift by very small angle from their orbit. But this small angle drift may result in large deviation from their original orbit over a long distance which these satellite covers over a period of time. For the course correction of these satellites, very small thrust is required in specific direction. Normal propulsion system cannot serve this purpose, because the thrust may be too large for these satellites. That’s where the role of micro thrusters becomes important. These are MEMS devices which can produce very small thrust and can be used for nano and micro satellite propulsion. In this study, we have developed micro thrusters using 3D printing technology from ceramic polymer composite. They have been characterized for different nano mechanical properties to study their suitability for propelling the nano and micro satellite.

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Wapman, Jonathan D., David C. Sternberg, Kevin Lo, Michael Wang, Laura Jones-Wilson, and Swati Mohan. "Jet Propulsion Laboratory Small Satellite Dynamics Testbed Planar Air-Bearing Propulsion System Characterization." Journal of Spacecraft and Rockets 58, no. 4 (July 2021): 954–71. http://dx.doi.org/10.2514/1.a34857.

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Gagne, Kevin, M. McDevitt, and Darren Hitt. "A Dual Mode Propulsion System for Small Satellite Applications." Aerospace 5, no. 2 (May 2, 2018): 52. http://dx.doi.org/10.3390/aerospace5020052.

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OKAMOTO, Hirouyki, Mitsuteru SUGIKI, and Shin SATORI. "A3 Development of the Electric Propulsion for Small Satellite." Proceedings of the Space Engineering Conference 2002.10 (2002): 9–12. http://dx.doi.org/10.1299/jsmesec.2002.10.9.

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Manente, M., F. Trezzolani, M. Magarotto, E. Fantino, A. Selmo, N. Bellomo, E. Toson, and D. Pavarin. "REGULUS: A propulsion platform to boost small satellite missions." Acta Astronautica 157 (April 2019): 241–49. http://dx.doi.org/10.1016/j.actaastro.2018.12.022.

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Romero-Diez, Sandra, Lydia Hantsche, Jason Pearl, Darren Hitt, M. McDevitt, and Patrick Lee. "A Single-Use Microthruster Concept for Small Satellite Attitude Control in Formation-Flying Applications." Aerospace 5, no. 4 (November 14, 2018): 119. http://dx.doi.org/10.3390/aerospace5040119.

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In recent years, the maturation of small satellite technology has led to their adoption for a variety of space missions. The next generation of small satellite missions, however, will likely have the satellites operating in formations or “constellations” to perform missions that are not currently possible. A key enabling technology for constellation-based missions is a miniaturized propulsion system that is capable of delivering the extremely low impulse levels required for maintaining precise relative position and orientation. Existing propulsion solutions for this regime suffer from compromises on power, safety, and cost that have limited their adoption. In this work, we describe a new, low-power micropropulsion concept based on the thermal decomposition of an inert chemical blowing agent (CBA) as the propellant. A meso-scale prototype device is designed, fabricated, and tested. The experimental results indicate that this concept, when appropriately scaled, is capable of providing thrust levels (∼1 μ N) and impulse-bits (∼0.1 μ N·s) that are commensurate with the intended application.

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Miller, Sara, Mitchell L. R. Walker, Jack Agolli, and John Dankanich. "Correction: Survey and Performance Evaluation of Small- Satellite Propulsion Technologies." Journal of Spacecraft and Rockets 58, no. 4 (July 2021): 1. http://dx.doi.org/10.2514/1.a34774.c1.

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Schmierer, Christian, Mario Kobald, Konstantin Tomilin, Ulrich Fischer, and Stefan Schlechtriem. "Low cost small-satellite access to space using hybrid rocket propulsion." Acta Astronautica 159 (June 2019): 578–83. http://dx.doi.org/10.1016/j.actaastro.2019.02.018.

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Anshakov, G. P., A. V. Krestina, and I. S. Tkachenko. "Analysis of the effectiveness of the de-orbiting devices for small satellite." Spacecrafts & Technologies 4, no. 2 (2020): 72–84. http://dx.doi.org/10.26732/j.st.2020.2.02.

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At present, the use of various methods is proposed for the de-orbit of small satellite, and the most feasible and promising of them are analyzed. The task of evaluating the effectiveness of the de-orbiting system for small satellite is set, in the framework of which a criterion and basic performance indicators are formed taking into account design features. As a methodological basis for evaluating the effectiveness, the method of relative integral assessment was used. Using the developed algorithm for calculating the coefficients of the integral relative assessment for each de-orbiting method, the most effective option for constructing the system isdetermined for given priority coefficients and taking into account the imposed design restrictions. For the analysis of efficiency, fuel-free de-orbiting devices and three types of propulsion systems were chosen – electric propulsion engine, solid rocket motor and liquid engine. Efficiency analysis was carried out for devices with various mass and target characteristics, the result is the choice of the type of de-orbiting system and the calculation of its parameters. The dependence of the de-orbiting device on the purpose of the spacecraft, the altitude and inclination of the orbit of its functioning, as well as on the requirements for mass, cost and other design parameters is shown.

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Zabolotnov, Yu M., V. V. Lyubimov, and E. V. Kurkina. "Evaluation of Asymmetric Small Satellite with Electric Propulsion Perturbations when Passing through Resonance." Procedia Engineering 185 (2017): 299–303. http://dx.doi.org/10.1016/j.proeng.2017.03.344.

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Sternberg, David C., Christopher Pong, Nuno Filipe, Swati Mohan, Shawn Johnson, and Laura Jones-Wilson. "Jet Propulsion Laboratory Small Satellite Dynamics Testbed Simulation: On-Orbit Performance Model Validation." Journal of Spacecraft and Rockets 55, no. 2 (March 2018): 322–34. http://dx.doi.org/10.2514/1.a33806.

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AOKI, Yoshinori, Shin SATORI, Atushi NAGATA, and Hiroyuki Okamoto. "509 EM design of the New-type Electric Propulsion for Small Satellite application." Proceedings of Conference of Hokkaido Branch 2000.40 (2000): 198–99. http://dx.doi.org/10.1299/jsmehokkaido.2000.40.198.

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Kestilä, Antti, Kalle Nordling, Ville Miikkulainen, Mikko Kaipio, Tuomas Tikka, Mika Salmi, Aleksi Auer, Markku Leskelä, and Mikko Ritala. "Towards space-grade 3D-printed, ALD-coated small satellite propulsion components for fluidics." Additive Manufacturing 22 (August 2018): 31–37. http://dx.doi.org/10.1016/j.addma.2018.04.023.

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Babuscia, Alessandra. "Telecommunication Systems for Small Satellites Operating at High Frequencies: A Review." Information 11, no. 5 (May 8, 2020): 258. http://dx.doi.org/10.3390/info11050258.

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Small Satellites and in particular CubeSats are becoming extremely popular platforms with which to perform space research. They allow for rapid prototyping with considerable cost savings with respect to traditional missions. However, as small satellite missions become more ambitious in terms of destinations to reach (from Low Earth Orbit to interplanetary) and in terms of the amount of data to transmit, new technologies need to be developed to provide adequate telecommunication support. This paper aims to review the telecommunication systems that have been developed at the Jet Propulsion Laboratory for some of the most recent CubeSat missions operating at different frequency bands: ASTERIA (S-Band), MarCO (X-Band and UHF) and ISARA (Ka-Band and UHF). For each of these missions: the telecommunication challenges and requirements are listed; the final system design is presented; the characteristics of the different hardware components are shown; and the lessons learned through operations are discussed.

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Sreesawet, Suwat, Seksan Jaturat, and Sittiporn Channamsin. "Orbit Design for Thai Space Consortium Satellite." Proceedings 39, no. 1 (December 27, 2019): 1. http://dx.doi.org/10.3390/proceedings2019039001.

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Currently, Geo-Informatics and Space Technology Development Agency (GISTDA), National Astronomical Research Institute of Thailand (NARIT) and Synchrotron Light Research Institute (SLRI) have a co-operation on a project of developing a satellite for scientific research called Thai Space Consortium (TSC). The project is aiming at Earth remote sensing mission by a small satellite about 100 kg. The main payload of the satellite is an optical instrument with the secondary payload of energetic particle detector for space weather. The satellite is designed to be in a Sun Synchronous orbit due to requirement of same light condition throughout the operational lifetime. In the meantime, there is another project by GISTDA named THEOS-2. This project consists of two remote-sensing satellites, THEOS-2 MainSAT and THEOS-2 SmallSAT, under the development in Europe. The SmallSAT does not have the propulsion subsystem. So it cannot perform station-keeping maneuvers or maintain constellation with others. Therefore, in this paper, we analyze two scenarios that the TSC satellite flies as constellations with the MainSAT of THEOS2 project. The constellation is in the sense that the TSC satellite flies on the same ground track path with the MainSAT satellite with slightly differences in local solar time. The ground track sequencing is presented with a methodology for obtaining orbital parameters with a discussion on accuracy relating to Keplerian assumption.

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Gomes, Vivian M., and Antonio F. B. A. Prado. "Low-Thrust Out-of-Plane Orbital Station-Keeping Maneuvers for Satellites." Mathematical Problems in Engineering 2012 (2012): 1–14. http://dx.doi.org/10.1155/2012/532708.

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This paper considers the problem of out of plane orbital maneuvers for station keeping of satellites. The main idea is to consider that a satellite is in an orbit around the Earth and that it has its orbit is disturbed by one or more forces. Then, it is necessary to perform a small amplitude orbital correction to return the satellite to its original orbit, to keep it performing its mission. A low thrust propulsion is used to complete this task. It is important to search for solutions that minimize the fuel consumption to increase the lifetime of the satellite. To solve this problem a hybrid optimal control approach is used. The accuracy of the satisfaction of the constraints is considered, in order to try to decrease the fuel expenditure by taking advantage of this freedom. This type of problem presents numerical difficulties and it is necessary to adjust parameters, as well as details of the algorithm, to get convergence. In this versions of the algorithm that works well for planar maneuvers are usually not adequate for the out of plane orbital corrections. In order to illustrate the method, some numerical results are presented.

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Kothnur, P. S., and L. L. Raja. "Simulation of Direct-Current Microdischarges for Application in Electro-Thermal Class of Small Satellite Propulsion Devices." Contributions to Plasma Physics 47, no. 1-2 (February 2007): 9–18. http://dx.doi.org/10.1002/ctpp.200710003.

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Volotsuev, V. V., and V. V. Salmin. "An Analysis of the Efficiency of Electric Propulsion Engines for Maintaining a Low Orbit of Small Spacecraft." Proceedings of Higher Educational Institutions. Маchine Building, no. 10 (727) (November 2020): 65–74. http://dx.doi.org/10.18698/0536-1044-2020-10-65-74.

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This paper examines the problem of maintaining the plane parameters of the working orbit of a small spacecraft using an electric propulsion engine. In low working orbits, due to the Earth’s atmosphere, a spacecraft is subjected to aerodynamic drag forces, which results in a decrease in the radius of the orbit and a potential termination of the useful target functioning. The time parameters of the cyclogram for maintaining the working orbit of a small spacecraft with an electric low thrust engine are analyzed taking into account the variability of the atmospheric density. The cyclogram consists of sections of the passive and active movement under the action of the low thrust engine. For the satellite under study, suitable thrust parameters of the electric engine are selected, which allow the correction of the plane parameters of the low orbit. Using the characteristics of the thrust and specific impulse of the electric jet engine, fuel reserves for correction over a long period of time are calculated. The results of the analysis confirm the effectiveness of the electric propulsion engine in terms of fuel consumption for correction.

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Szelecka, Agnieszka, Jacek Kurzyna, Dariusz Daniłko, and Serge Barral. "Liquid micro pulsed plasma thruster." Nukleonika 60, no. 2 (June 1, 2015): 257–61. http://dx.doi.org/10.1515/nuka-2015-0057.

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Abstract A new type of pulsed plasma thruster (PPT) for small satellite propulsion is investigated, of which the most innovative aspect is the use of a non-volatile liquid propellant. The thruster is based on an open capillary design. The thruster achieved a thrust-to-power ratio above 45 μN/W, which constitutes a 5-fold improvement over the water-propelled pulsed plasma thruster, and which is also slightly above the performance of a similarly sized PPT with a solid propellant.

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Kim, Younho, Seokhyun Kang, Yunhwang Jung, Seongmin Kang, Jongho Seon, Sang-Hyun Lee, Won-Ho Cha, and Hee-Kwang Eun. "Launch Environment Test and Evaluation of Fuel Feeding Unit for Electric Propulsion System to Small-Satellite Applications." Journal of the Korean Society for Aeronautical & Space Sciences 42, no. 12 (December 1, 2014): 1051–56. http://dx.doi.org/10.5139/jksas.2014.42.12.1051.

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Wieth-Knudsen, Niels P. "Wanted: An International Jovian-Satellite-Phenomenon Centre." International Astronomical Union Colloquium 98 (1988): 199. http://dx.doi.org/10.1017/s0252921100092873.

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AbstractAmateur observations made since 1977 show that although the ephemerides for the satellites of Jupiter published by the Jet Propulsion Laboratory are more accurate than those in the Astronomical Almanac, there are still small deviations, which may increase with time. Observation of eclipses, transits and occultations, as well as of the mutual phenomena that occur at 6-yearly intervals can provide information for correction of the ephemerides. There appear to be three groups coordinating observations: 1) in Germany, started by P. Ahnert in the early 1960s and now under H.-J. Blasberg; 2) in the U.S.A., started by J. Ashbrook in 1976, and continued by J. Westfall of the ALPO; 3) in Australia and New Zealand, led by B. Loader. These groups appear to work independently, and it would greatly help research on this subject if there were an International Centre for collecting observations of the Jovian satellites – perhaps under the supervision of the IAU – whereby all observations made anywhere in the world would be available to anyone investigating the subject. Paris, where the predictions are calculated, might be a very suitable site for such a centre.

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Governale, G., J. Rimani, N. Viola, and V. Fernandez Villace. "A trade-off methodology for micro-launchers." Aerospace Systems 4, no. 3 (May 27, 2021): 209–26. http://dx.doi.org/10.1007/s42401-021-00095-w.

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AbstractThe trend of cost-effective access to space and satellite technologies’ evolution is increasing the small satellite market. However, small payloads usually ride as piggyback, being a secondary passenger of a space vector, with very low flexibility in target orbit and launch schedule. The micro-launchers are designed to answer the needs of the small satellite missions, with a payload capacity up to 350 kg to Low Earth Orbit, aiming to low turn-over time and competitive prices. This paper explains the work performed by Politecnico di Torino in support of the ESA–ESTEC activities on micro-launchers. The aim is to provide preliminary guidelines for choosing and evaluating new innovative micro-launcher flight vehicle engineering processes. A trade-off methodology is proposed and defined based on the Analytically Hierarchical Process (AHP). This methodology considers, among other features, the flight profile, maximum payload, and physical characteristics. To support the trade-off analysis, a software tool is built for the automatic generation of the aerodynamics and propulsion parameters needed for the completion of the preliminary designs, enabling the performance estimation. The launcher’s performance models, with an analysis of the take-off sites and target orbits, are also produced. This allows the definition of performance maps where the maximum payload is graphed as a function of the orbit altitude and inclination. A set of innovative micro-launchers exploiting different technologies is also assessed as a case study.

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Chelaru, Teodor Viorel, Valentin Pana, and Adrian Chelaru. "Modelling and Simulation of Suborbital Launcher for Testing." Applied Mechanics and Materials 555 (June 2014): 32–39. http://dx.doi.org/10.4028/www.scientific.net/amm.555.32.

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The purpose of this paper is to present some aspects regarding the computational model and technical solutions for multistage suborbital launcher for testing (SLT) used to test spatial equipment and scientific measurements. The computational model consists in numerical simulation of SLT evolution for different start conditions. The launcher model presented will be with six degrees of freedom (6DOF) and variable mass. The results analysed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize a small multi-stage launcher, by recycling military rocket motors. From technical point of view, the paper is focused on national project “Suborbital Launcher for Testing” (SLT), which is based on hybrid propulsion and control systems, obtained through an original design. Therefore, while classical suborbital sounding rockets are unguided and they use as propulsion solid fuel motor having an uncontrolled ballistic flight, SLT project is introducing a different approach, by proposing the creation of a guided suborbital launcher, which is basically a satellite launcher at a smaller scale, containing its main subsystems. This is why the project itself can be considered an intermediary step in the development of a wider range of launching systems based on hybrid propulsion technology, which may have a major impact in the future European launchers programs. SLT project, as it is shown in the title, has two major objectives: first, a short term objective, which consists in obtaining a suborbital launching system which will be able to go into service in a predictable period of time, and a long term objective that consists in the development and testing of some unconventional sub-systems which will be integrated later in the satellite launcher as a part of the European space program. This is why the technical content of the project must be carried out beyond the range of the existing suborbital vehicle programs towards the current technological necessities in the space field, especially the European one.

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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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Cao, Anzhou, Yanqiu Gao, Jicai Zhang, and Xianqing Lv. "Trajectory Estimation of Aircraft in a Double-Satellite Passive Positioning System with the Adjoint Method." Mathematical Problems in Engineering 2013 (2013): 1–7. http://dx.doi.org/10.1155/2013/502610.

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A double-satellite passive positioning system is constructed based on the theory of space geometry, where two observation coordinate systems and a fundamental coordinate system exist. In each observation coordinate system, there exists a ray from the observation satellite to the aircraft. One difficulty lies in that these two rays may not intersect due to the existence of various errors. Under this situation, this work assumes that the middle point of common perpendicular between two rays is the actual position of aircraft. Based on the theory of space geometry, the coordinates of aircraft in the fundamental coordinate system can be determined. A dynamic model with the adjoint method is developed to estimate the trajectory of aircraft during the process of rocket propulsion. By assimilating observations, the trajectory of aircraft can be calculated. Numerical experiments are designed to validate the reasonability and feasibility of this model. Simulated results indicate that even by assimilating a small number of observations, the trajectory of aircraft can be estimated. In addition, the trajectory estimation can become more accurate when more observations are assimilated to the model.

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Kaizu, Yutaka, Tetsuo Shimada, Yusuke Takahashi, Sho Igarashi, Hiroyuki Yamada, Kenichi Furuhashi, and Kenji Imou. "Development of a Small Electric Robot Boat for Mowing Aquatic Weeds." Transactions of the ASABE 64, no. 3 (2021): 1073–82. http://dx.doi.org/10.13031/trans.14295.

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HighlightsA small, automatically guided electric robot boat was developed to control the growth of aquatic plants in lakes.The robot boat was able to mow without becoming entangled with aquatic plants due to the paddle propulsion mechanism.The average speed was 0.41 m s-1, and the lateral deviation from the set path was 9.4 cm.The growth restraint effect was confirmed using aerial images collected by a drone.Abstract. At present, aquatic plants are becoming a problem in various lakes. Aquatic weeds that grow to high densities cause decreases in the oxygen concentration in the water, accumulation of sludge, and adverse effects on water use facilities and fisheries. Although there are large machines for cutting and harvesting aquatic plants, their use is limited due to their high cost, large size, and heavy weight. On the other hand, manual cutting is very labor intensive and inefficient. Therefore, in this research, we developed a labor-saving and low-cost robot boat to mow aquatic plants. This robot boat is automatically controlled by a real-time kinematic global navigational satellite system (RTK-GNSS) and is characterized by its small size, light weight, excellent portability, and low energy consumption. In addition, a paddle mechanism that replaces a conventional propeller was introduced as a propulsion mechanism to prevent entanglement of water plants and enable long-term automatic navigation. Mowing lotus (Nelumbo nucifera) in Lake Izunuma, Miyagi prefecture, Japan, confirmed that mowing could be properly conducted with a lateral deviation of 9.4 cm, average speed of 0.41 m s-1, and average power consumption of 518 W even when lotus was at its densest growth. If the cutting width of the robot boat was 1.2 m and the sidelap width was 0.3 m, the theoretical field work rate would be 0.133 ha h-1. Images captured by a drone confirmed that cutting with the robot boat was effective in suppressing the growth of lotus. It was found that the effect of suppressing growth was maximized by mowing at the time when the stopping leaves appeared in the late growth stage of lotus. Keywords: Autonomous navigation, Lotus, Moving baseline, Robot operation system, RTK-GNSS, Virtual private network.

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Lukin, Alexander. "New insights into the reactionary zones excited-state programming by plasma-acoustic coupling mechanism for the next-generation small satellite solid propulsion systems." Journal of Physics: Conference Series 1507 (March 2020): 022006. http://dx.doi.org/10.1088/1742-6596/1507/2/022006.

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Sun, Ran, Aidang Shan, Chengxi Zhang, and Qingxian Jia. "Spacecraft formation control using aerodynamic and Lorentz force." Aircraft Engineering and Aerospace Technology 92, no. 4 (March 18, 2020): 587–97. http://dx.doi.org/10.1108/aeat-10-2019-0207.

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Purpose This paper aims to investigate the feasibility of using the combination of Lorentz force and aerodynamic force as a propellantless control method for spacecraft formation. Design/methodology/approach It is assumed that each spacecraft is equipped with several large flat plates, which can rotate to produce aerodynamic force. Lorentz force can be achieved by modulating spacecraft’s electrostatic charge. An adaptive output feedback controller is designed based on a sliding mode observer to account for unknown uncertainties and the absence of relative velocity measurements. Aiming at distributing the control input, an optimal control allocation method is proposed to calculate the electrostatic charge of the Lorentz spacecraft and control commands for the atmospheric-based actuators. Findings Numerical examples are provided to demonstrate the effectiveness of the proposed control strategy in the presence of J2 perturbations. Simulation results show that relative motion in a formation can be precisely controlled by the proposed propellantless control method under uncertainties and unavailability of velocity measurements. Research limitations/implications The controllability of the system is not theoretically investigated in the current work. Practical implications The proposed control method introduced in this paper can be applied for small satellites formation in low Earth orbit. Originality/value The main contribution of the paper is the proposal of the propellantless control approach for satellite formation using the combination of Lorentz force and aerodynamic force, which can eliminate the requirement of the propulsion system.

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Cucurull, L., R. Atlas, R. Li, M. J. Mueller, and R. N. Hoffman. "An Observing System Simulation Experiment with a Constellation of Radio Occultation Satellites." Monthly Weather Review 146, no. 12 (November 26, 2018): 4247–59. http://dx.doi.org/10.1175/mwr-d-18-0089.1.

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Abstract Experiments with a global observing system simulation experiment (OSSE) system based on the recent 7-km-resolution NASA nature run (G5NR) were conducted to determine the potential value of proposed Global Navigation Satellite System (GNSS) radio occultation (RO) constellations in current operational numerical weather prediction systems. The RO observations were simulated with the geographic sampling expected from the original planned Constellation Observing System for Meteorology, Ionosphere, and Climate-2 (COSMIC-2) system, with six equatorial (total of ~6000 soundings per day) and six polar (total of ~6000 soundings per day) receiver satellites. The experiments also accounted for the expected improved vertical coverage provided by the Jet Propulsion Laboratory RO receivers on board COSMIC-2. Except that RO observations were simulated and assimilated as refractivities, the 2015 version of the NCEP’s operational data assimilation system was used to run the OSSEs. The OSSEs quantified the impact of RO observations on global weather analyses and forecasts and the impact of adding explicit errors to the simulation of perfect RO profiles. The inclusion or exclusion of explicit errors had small, statistically insignificant impacts on results. The impact of RO observations was found to increase the length of the useful forecasts. In experiments with explicit errors, these increases were found to be 0.6 h in the Northern Hemisphere extratropics (a 0.4% improvement), 5.9 h in the Southern Hemisphere extratropics (a significant 4.0% improvement), and 12.1 h in the tropics (a very substantial 28.4% improvement).

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Aragon, Bruno, Rasmus Houborg, Kevin Tu, Joshua B. Fisher, and Matthew McCabe. "CubeSats Enable High Spatiotemporal Retrievals of Crop-Water Use for Precision Agriculture." Remote Sensing 10, no. 12 (November 22, 2018): 1867. http://dx.doi.org/10.3390/rs10121867.

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Remote sensing based estimation of evapotranspiration (ET) provides a direct accounting of the crop water use. However, the use of satellite data has generally required that a compromise between spatial and temporal resolution is made, i.e., one could obtain low spatial resolution data regularly, or high spatial resolution occasionally. As a consequence, this spatiotemporal trade-off has tended to limit the impact of remote sensing for precision agricultural applications. With the recent emergence of constellations of small CubeSat-based satellite systems, these constraints are rapidly being removed, such that daily 3 m resolution optical data are now a reality for earth observation. Such advances provide an opportunity to develop new earth system monitoring and assessment tools. In this manuscript we evaluate the capacity of CubeSats to advance the estimation of ET via application of the Priestley-Taylor Jet Propulsion Laboratory (PT-JPL) retrieval model. To take advantage of the high-spatiotemporal resolution afforded by these systems, we have integrated a CubeSat derived leaf area index as a forcing variable into PT-JPL, as well as modified key biophysical model parameters. We evaluate model performance over an irrigated farmland in Saudi Arabia using observations from an eddy covariance tower. Crop water use retrievals were also compared against measured irrigation from an in-line flow meter installed within a center-pivot system. To leverage the high spatial resolution of the CubeSat imagery, PT-JPL retrievals were integrated over the source area of the eddy covariance footprint, to allow an equivalent intercomparison. Apart from offering new precision agricultural insights into farm operations and management, the 3 m resolution ET retrievals were shown to explain 86% of the observed variability and provide a relative RMSE of 32.9% for irrigated maize, comparable to previously reported satellite-based retrievals. An observed underestimation was diagnosed as a possible misrepresentation of the local surface moisture status, highlighting the challenge of high-resolution modeling applications for precision agriculture and informing future research directions. .

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Keidar, Michael, Taisen Zhuang, Alexey Shashurin, George Teel, Dereck Chiu, Joseph Lukas, Samudra Haque, and Lubos Brieda. "Electric propulsion for small satellites." Plasma Physics and Controlled Fusion 57, no. 1 (November 28, 2014): 014005. http://dx.doi.org/10.1088/0741-3335/57/1/014005.

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Arief, Syachrul, and Andrea Gatti. "Analyzing the Tropospheric Delay Estimates on Global Navigation Satellite Systems (GNSS) with Precise Point Positioning (PPP) Services using the goGPS software." JGISE: Journal of Geospatial Information Science and Engineering 3, no. 2 (November 25, 2020): 79. http://dx.doi.org/10.22146/jgise.56071.

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The tropospheric delay is an essential source of error for positioning using the Global Navigation Satellite System (GNSS). Scientific applications of GNSS positioning such as the study of earth crust deformation and earthquake prediction require high accuracy in positioning, an analysis of tropospheric delay calculations is needed to improve the accuracy of GNSS positioning. One part of the tropospheric delay is Zenith tropospheric delays (ZTD), which are estimated using the Precise Point Positioning (PPP) method. ZTD estimates can be beneficial for meteorological applications, for example, is the estimation of water vapor levels in the atmosphere from the estimated ZTD. We use GNSS data from the BAKO station in Cibinong and JOG2 station located in Yogyakarta. The GNSS data format is an Independent Exchange Receiver (RINEX), which we extracted using the sophisticated open-source GNSS software, called goGPS version 1.0 Beta from Geomatics Research and Development s.r.l. - Lomazzo, Italy. We validate the results of the extraction process with two international tropospheric products from International GNSS Services (IGS) with commercial software Bernese version 5 and the University of Nevada Reno (UNR) with software from NASA Jet Propulsion Laboratory (JPL) namely GIPSY / OASIS II. Epoch in this study, we use days of the year (DOY) 022-025 / 22-25 January representing the rainy season and DOY 230-233 to coincide on August 17-20 representing the dry season 2018. Our results obtained ZTD values both in January and August, and the two BAKO and JOG2 stations were consistent and worked well at different times and stations. RMS throughout DOY, both at BAKO and JOG2 stations, show small values <2 mm. The RMS value is relatively small, meaning that the troposphere estimation process with goGPS shows a good agreement because it is almost the same as the international troposphere products from UNR and IGS. This means that the ZTD estimation process from goGPS software can be an alternative to paid software. The range of ZTD values in January tends to be higher than in August, meaning the value of ZTD has a strong correlation with changes in the rainy and dry seasons, this shows that ZTD can be useful for meteorological purposes.

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O’Reilly, Dillon, Georg Herdrich, and Darren F. Kavanagh. "Electric Propulsion Methods for Small Satellites: A Review." Aerospace 8, no. 1 (January 18, 2021): 22. http://dx.doi.org/10.3390/aerospace8010022.

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Over 2500 active satellites are in orbit as of October 2020, with an increase of ~1000 smallsats in the past two years. Since 2012, over 1700 smallsats have been launched into orbit. It is projected that by 2025, there will be 1000 smallsats launched per year. Currently, these satellites do not have sufficient delta v capabilities for missions beyond Earth orbit. They are confined to their pre-selected orbit and in most cases, they cannot avoid collisions. Propulsion systems on smallsats provide orbital manoeuvring, station keeping, collision avoidance and safer de-orbit strategies. In return, this enables longer duration, higher functionality missions beyond Earth orbit. This article has reviewed electrostatic, electrothermal and electromagnetic propulsion methods based on state of the art research and the current knowledge base. Performance metrics by which these space propulsion systems can be evaluated are presented. The article outlines some of the existing limitations and shortcomings of current electric propulsion thruster systems and technologies. Moreover, the discussion contributes to the discourse by identifying potential research avenues to improve and advance electric propulsion systems for smallsats. The article has placed emphasis on space propulsion systems that are electric and enable interplanetary missions, while alternative approaches to propulsion have also received attention in the text, including light sails and nuclear electric propulsion amongst others.

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Panelli, Mario, Davide Morfei, Beniamino Milo, Francesco D’Aniello, and Francesco Battista. "Axisymmetric Hybrid Plasma Model for Hall Effect Thrusters." Particles 4, no. 2 (June 18, 2021): 296–324. http://dx.doi.org/10.3390/particles4020026.

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Hall Effect Thrusters (HETs) are nowadays widely used for satellite applications because of their efficiency and robustness compared to other electric propulsion devices. Computational modelling of plasma in HETs is interesting for several reasons: it can be used to predict thrusters’ operative life; moreover, it provides a better understanding of the physical behaviour of this device and can be used to optimize the next generation of thrusters. In this work, the discharge within the accelerating channel and near-plume of HETs has been modelled by means of an axisymmetric hybrid approach: a set of fluid equations for electrons has been solved to get electron temperatures, plasma potential and the discharge current, whereas a Particle-In-Cell (PIC) sub-model has been developed to capture the behaviour of neutrals and ions. A two-region electron mobility model has been incorporated. It includes electron–neutral/ion collisions and uses empirical constants, that vary as a continuous function of axial coordinates, to take into account electron–wall collisions and Bohm diffusion/SEE effects. An SPT-100 thruster has been selected for the verification of the model because of the availability of reliable numerical and experimental data. The results of the presented simulations show that the code is able to describe plasma discharge reproducing, with consistency, the physics within the accelerating channel of HETs. A small discrepancy in the experimental magnitude of ions’ expansion, due probably to boundary condition effects, has been found.

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Chouza, Fernando, Thierry Leblanc, John Barnes, Mark Brewer, Patrick Wang, and Darryl Koon. "Long-term (1999–2019) variability of stratospheric aerosol over Mauna Loa, Hawaii, as seen by two co-located lidars and satellite measurements." Atmospheric Chemistry and Physics 20, no. 11 (June 10, 2020): 6821–39. http://dx.doi.org/10.5194/acp-20-6821-2020.

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Abstract. As part of the Network for the Detection of Atmospheric Composition Change (NDACC), ground-based measurements obtained from the Jet Propulsion Laboratory (JPL) stratospheric ozone lidar and the NOAA stratospheric aerosol lidar at Mauna Loa, Hawaii, over the past 2 decades were used to investigate the impact of volcanic eruptions and pyrocumulonimbus (PyroCb) smoke plumes on the stratospheric aerosol load above Hawaii since 1999. Measurements at 355 and 532 nm conducted by these two lidars revealed a color ratio of 0.5 for background aerosols and small volcanic plumes and 0.8 for a PyroCb plume recorded on September 2017. Measurements of the Nabro plume by the JPL lidar in 2011–2012 showed a lidar ratio of (64±12.7) sr at 355 nm around the center of the plume. The new Global Space-based Stratospheric Aerosol Climatology (GloSSAC), Cloud-Aerosol Lidar with Orthogonal Polarization (CALIOP) Level 3 and Stratospheric Aerosol and Gas Experiment III on the International Space Station (SAGE III-ISS) stratospheric aerosol datasets were compared to the ground-based lidar datasets. The intercomparison revealed a generally good agreement, with vertical profiles of extinction coefficient within 50 % discrepancy between 17 and 23 km above sea level (a.s.l.) and 25 % above 23 km a.s.l. The stratospheric aerosol depth derived from all of these datasets shows good agreement, with the largest discrepancy (20 %) being observed between the new CALIOP Level 3 and the other datasets. All datasets consistently reveal a relatively quiescent period between 1999 and 2006, followed by an active period of multiple eruptions (e.g., Nabro) until early 2012. Another quiescent period, with slightly higher aerosol background, lasted until mid-2017, when a combination of extensive wildfires and multiple volcanic eruptions caused a significant increase in stratospheric aerosol loading. This loading maximized at the very end of the time period considered (fall 2019) as a result of the Raikoke eruption, the plume of which ascended to 26 km altitude in less than 3 months.

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D., Hassan, Argoun B., Elbayoumi G., and Omer m. "ORBIT MAINTENANCE FOR SMALL SATELLITES USING ELECTRIC PROPULSION." International Conference on Aerospace Sciences and Aviation Technology 9, ASAT Conference, 8-10 May 2001 (May 1, 2001): 1–16. http://dx.doi.org/10.21608/asat.2001.31154.

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D., Hassan, Argoun B., Elbayoumi G., and Omer M. "ORBIT MAINTENANCE FOR SMALL SATELLITES USING ELECTRIC PROPULSION." International Conference on Aerospace Sciences and Aviation Technology 9, no. 9 (May 1, 2001): 1017–32. http://dx.doi.org/10.21608/asat.2001.59793.

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Fersch, Benjamin, Harald Kunstmann, András Bárdossy, Balaji Devaraju, and Nico Sneeuw. "Continental-Scale Basin Water Storage Variation from Global and Dynamically Downscaled Atmospheric Water Budgets in Comparison with GRACE-Derived Observations." Journal of Hydrometeorology 13, no. 5 (October 1, 2012): 1589–603. http://dx.doi.org/10.1175/jhm-d-11-0143.1.

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Abstract Since 2002, the Gravity Recovery and Climate Experiment (GRACE) has provided gravity-derived observations of variations in the terrestrial water storage. Because of the lack of suitable direct observations of large-scale water storage changes, a validation of the GRACE observations remains difficult. An approach that allows the evaluation of terrestrial water storage variations from GRACE by a comparison with those derived from aerologic water budgets using the atmospheric moisture flux divergence is presented. In addition to reanalysis products from the European Centre for Medium-Range Weather Forecasts and the National Centers for Environmental Prediction, high-resolution regional atmospheric simulations were produced with the Weather Research and Forecast modeling system (WRF) and validated against globally gridded observational data of precipitation and 2-m temperature. The study encompasses six different climatic and hydrographic regions: the Amazon basin, the catchments of Lena and Yenisei, central Australia, the Sahara, the Chad depression, and the Niger. Atmospheric-related uncertainty bounds based on the range of the ensemble of estimated terrestrial water storage variations were computed using different configurations of the regional climate model WRF and different global reanalyses. Atmospheric-related uncertainty ranges with those originating from the GRACE products of GeoForschungsZentrum Potsdam, the Center for Space Research, and the Jet Propulsion Laboratory were also compared. It is shown that dynamically downscaled atmospheric fields are able to add value to global reanalyses, depending on the geographical location of the considered catchments. Global and downscaled atmospheric water budgets are in reasonable agreement (r ≈ 0.7 − 0.9) with GRACE-derived terrestrial mass variations. However, atmospheric- and satellite-based approaches show shortcomings for regions with small storage change rates (<20–25 mm month−1).

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Maisonneuve, V., J. C. Godon, Renaud Lecourt, G. Lengelle, and N. Pillet. "HYBRID PROPULSION FOR SMALL SATELLITES DESIGN LOGIC AND TESTS." International Journal of Energetic Materials and Chemical Propulsion 5, no. 1-6 (2002): 90–100. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v5.i1-6.130.

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Gibbon, D., C. Underwood, M. Sweeting, and R. Amri. "Cost effective propulsion systems for small satellites using butane propellant." Acta Astronautica 51, no. 1-9 (July 2002): 145–52. http://dx.doi.org/10.1016/s0094-5765(02)00074-7.

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Dowdeswell, J. A., J. Evans, R. Mugford, G. Griffiths, S. McPhail, N. Millard, P. Stevenson, et al. "Autonomous underwater vehicles (AUVs) and investigations of the ice–ocean interface in Antarctic and Arctic waters." Journal of Glaciology 54, no. 187 (2008): 661–72. http://dx.doi.org/10.3189/002214308786570773.

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AbstractLimitations of access have long restricted exploration and investigation of the cavities beneath ice shelves to a small number of drillholes. Studies of sea-ice underwater morphology are limited largely to scientific utilization of submarines. Remotely operated vehicles, tethered to a mother ship by umbilical cable, have been deployed to investigate tidewater-glacier and ice-shelf margins, but their range is often restricted. The development of free-flying autonomous underwater vehicles (AUVs) with ranges of tens to hundreds of kilometres enables extensive missions to take place beneath sea ice and floating ice shelves. Autosub2 is a 3600 kg, 6.7 m long AUV, with a 1600 m operating depth and range of 400 km, based on the earlier Autosub1 which had a 500 m depth limit. A single direct-drive d.c. motor and five-bladed propeller produce speeds of 1–2 m s−1. Rear-mounted rudder and stern-plane control yaw, pitch and depth. The vehicle has three sections. The front and rear sections are free-flooding, built around aluminium extrusion space-frames covered with glass-fibre reinforced plastic panels. The central section has a set of carbon-fibre reinforced plastic pressure vessels. Four tubes contain batteries powering the vehicle. The other three house vehicle-control systems and sensors. The rear section houses subsystems for navigation, control actuation and propulsion and scientific sensors (e.g. digital camera, upward-looking 300 kHz acoustic Doppler current profiler, 200 kHz multibeam receiver). The front section contains forward-looking collision sensor, emergency abort, the homing systems, Argos satellite data and location transmitters and flashing lights for relocation as well as science sensors (e.g. twin conductivity–temperature–depth instruments, multibeam transmitter, sub-bottom profiler, AquaLab water sampler). Payload restrictions mean that a subset of scientific instruments is actually in place on any given dive. The scientific instruments carried on Autosub are described and examples of observational data collected from each sensor in Arctic or Antarctic waters are given (e.g. of roughness at the underside of floating ice shelves and sea ice).

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Nosseir, Ahmed E. S., Angelo Cervone, and Angelo Pasini. "Modular Impulsive Green Monopropellant Propulsion System (MIMPS-G): For CubeSats in LEO and to the Moon." Aerospace 8, no. 6 (June 19, 2021): 169. http://dx.doi.org/10.3390/aerospace8060169.

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Green propellants are currently considered as enabling technology that is revolutionizing the development of high-performance space propulsion, especially for small-sized spacecraft. Modern space missions, either in LEO or interplanetary, require relatively high-thrust and impulsive capabilities to provide better control on the spacecraft, and to overcome the growing challenges, particularly related to overcrowded LEOs, and to modern space application orbital maneuver requirements. Green monopropellants are gaining momentum in the design and development of small and modular liquid propulsion systems, especially for CubeSats, due to their favorable thermophysical properties and relatively high performance when compared to gaseous propellants, and perhaps simpler management when compared to bipropellants. Accordingly, a novel high-thrust modular impulsive green monopropellant propulsion system with a micro electric pump feed cycle is proposed. MIMPS-G500mN is designed to be capable of delivering 0.5 N thrust and offers theoretical total impulse Itot from 850 to 1350 N s per 1U and >3000 N s per 2U depending on the burnt monopropellant, which makes it a candidate for various LEO satellites as well as future Moon missions. Green monopropellant ASCENT (formerly AF-M315E), as well as HAN and ADN-based alternatives (i.e., HNP225 and LMP-103S) were proposed in the preliminary design and system analysis. The article will present state-of-the-art green monopropellants in the (EIL) Energetic Ionic Liquid class and a trade-off study for proposed propellants. System analysis and design of MIMPS-G500mN will be discussed in detail, and the article will conclude with a market survey on small satellites green monopropellant propulsion systems and commercial off-the-shelf thrusters.

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Tang, Hai-Bin, Zhen-Peng Zi, Xiao-Wei Jin, Jian Jiang, Yu Zou, and Zhi-Yong Yan. "Design and Development: A Micro-Propulsion System with Propane Propellant for Small Satellites." Advanced Science Letters 4, no. 6 (July 1, 2011): 2015–21. http://dx.doi.org/10.1166/asl.2011.1600.

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Whiteman, David N., Kurt Rush, Scott Rabenhorst, Wayne Welch, Martin Cadirola, Gerry McIntire, Felicita Russo, et al. "Airborne and Ground-Based Measurements Using a High-Performance Raman Lidar." Journal of Atmospheric and Oceanic Technology 27, no. 11 (November 1, 2010): 1781–801. http://dx.doi.org/10.1175/2010jtecha1391.1.

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Abstract A high-performance Raman lidar operating in the UV portion of the spectrum has been used to acquire, for the first time using a single lidar, simultaneous airborne profiles of the water vapor mixing ratio, aerosol backscatter, aerosol extinction, aerosol depolarization and research mode measurements of cloud liquid water, cloud droplet radius, and number density. The Raman Airborne Spectroscopic Lidar (RASL) system was installed in a Beechcraft King Air B200 aircraft and was flown over the mid-Atlantic United States during July–August 2007 at altitudes ranging between 5 and 8 km. During these flights, despite suboptimal laser performance and subaperture use of the telescope, all RASL measurement expectations were met, except that of aerosol extinction. Following the Water Vapor Validation Experiment—Satellite/Sondes (WAVES_2007) field campaign in the summer of 2007, RASL was installed in a mobile trailer for ground-based use during the Measurements of Humidity and Validation Experiment (MOHAVE-II) field campaign held during October 2007 at the Jet Propulsion Laboratory’s Table Mountain Facility in southern California. This ground-based configuration of the lidar hardware is called Atmospheric Lidar for Validation, Interagency Collaboration and Education (ALVICE). During the MOHAVE-II field campaign, during which only nighttime measurements were made, ALVICE demonstrated significant sensitivity to lower-stratospheric water vapor. Numerical simulation and comparisons with a cryogenic frost-point hygrometer are used to demonstrate that a system with the performance characteristics of RASL–ALVICE should indeed be able to quantify water vapor well into the lower stratosphere with extended averaging from an elevated location like Table Mountain. The same design considerations that optimize Raman lidar for airborne use on a small research aircraft are, therefore, shown to yield significant dividends in the quantification of lower-stratospheric water vapor. The MOHAVE-II measurements, along with numerical simulation, were used to determine that the likely reason for the suboptimal airborne aerosol extinction performance during the WAVES_2007 campaign was a misaligned interference filter. With full laser power and a properly tuned interference filter, RASL is shown to be capable of measuring the main water vapor and aerosol parameters with temporal resolutions of between 2 and 45 s and spatial resolutions ranging from 30 to 330 m from a flight altitude of 8 km with precision of generally less than 10%, providing performance that is competitive with some airborne Differential Absorption Lidar (DIAL) water vapor and High Spectral Resolution Lidar (HSRL) aerosol instruments. The use of diode-pumped laser technology would improve the performance of an airborne Raman lidar and permit additional instrumentation to be carried on board a small research aircraft. The combined airborne and ground-based measurements presented here demonstrate a level of versatility in Raman lidar that may be impossible to duplicate with any other single lidar technique.

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Nosseir, Ahmed E. S., Angelo Cervone, and Angelo Pasini. "Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers." Aerospace 8, no. 1 (January 15, 2021): 20. http://dx.doi.org/10.3390/aerospace8010020.

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Current research trends have advanced the use of “green propellants” on a wide scale for spacecraft in various space missions; mainly for environmental sustainability and safety concerns. Small satellites, particularly micro and nanosatellites, evolved from passive planetary-orbiting to being able to perform active orbital operations that may require high-thrust impulsive capabilities. Thus, onboard primary and auxiliary propulsion systems capable of performing such orbital operations are required. Novelty in primary propulsion systems design calls for specific attention to miniaturization, which can be achieved, along the above-mentioned orbital transfer capabilities, by utilizing green monopropellants due to their relative high performance together with simplicity, and better storability when compared to gaseous and bi-propellants, especially for miniaturized systems. Owing to the ongoing rapid research activities in the green-propulsion field, it was necessary to extensively study and collect various data of green monopropellants properties and performance that would further assist analysts and designers in the research and development of liquid propulsion systems. This review traces the history and origins of green monopropellants and after intensive study of physicochemical properties of such propellants it was possible to classify green monopropellants to three main classes: Energetic Ionic Liquids (EILs), Liquid NOx Monopropellants, and Hydrogen Peroxide Aqueous Solutions (HPAS). Further, the tabulated data and performance comparisons will provide substantial assistance in using analysis tools—such as: Rocket Propulsion Analysis (RPA) and NASA CEA—for engineers and scientists dealing with chemical propulsion systems analysis and design. Some applications of green monopropellants were discussed through different propulsion systems configurations such as: multi-mode, dual mode, and combined chemical–electric propulsion. Although the in-space demonstrated EILs (i.e., AF-M315E and LMP-103S) are widely proposed and utilized in many space applications, the investigation transpired that NOx fuel blends possess the highest performance, while HPAS yield the lowest performance even compared to hydrazine.

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Baker, Adam M., Alex da Silva Curiel, Jake Schaffner, and Martin Sweeting. "“You can get there from here”: Advanced low cost propulsion concepts for small satellites beyond LEO." Acta Astronautica 57, no. 2-8 (July 2005): 288–301. http://dx.doi.org/10.1016/j.actaastro.2005.03.046.

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Leverone, Fiona, Angelo Cervone, Matteo Pini, and Eberhard Gill. "Design and characterisation of a bi-modal solar thermal propulsion and power system for small satellites." Applied Thermal Engineering 189 (May 2021): 116609. http://dx.doi.org/10.1016/j.applthermaleng.2021.116609.

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Journal articles on the topic 'Small Satellite Propulsion'

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