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Relevant bibliographies by topics / Small Satellite Propulsion

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Academic literature on the topic 'Small Satellite Propulsion'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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Journal articles on the topic "Small Satellite Propulsion"

1

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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Dissertations / Theses on the topic "Small Satellite Propulsion"

1

Zakirov, V. A. "Investigation into nitrous oxide propulsion option for small satellite applications." Thesis, University of Surrey, 2001. http://epubs.surrey.ac.uk/797406/.

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Armstrong, Isaac W. "Development and Testing of Additively Manufactured Aerospike Nozzles for Small Satellite Propulsion." DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7428.

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Automatic altitude compensation has been a holy grail of rocket propulsion for decades. Current state-of-the-art bell nozzles see large performance decreases at low altitudes, limiting rocket designs, shrinking payloads, and overall increasing costs. Aerospike nozzles are an old idea from the 1960’s that provide superior altitude-compensating performance and enhanced performance in vacuum, but have survivability issues that have stopped their application in satellite propulsion systems. A growing need for CubeSat propulsion systems provides the impetus to study aerospike nozzles in this application. This study built two aerospike nozzles using modern 3D metal printing techniques to test aerospikes at a size small enough to be potentially used on a CubeSat. Results indicated promising in-space performance, but further testing to determine thermal limits is deemed necessary.

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Boyd, Austin Walker. "Design considerations for the ORION satellite: structure, propulsion and attitude control subsystems for a small, general purpose spacecraft." Thesis, Monterey, California. Naval Postgraduate School, 1988. http://hdl.handle.net/10945/23156.

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A general purpose satellite (ORION) has been designed which will launch from the Space Shuttle using a NASA Get-Away-Special (GAS) canister. The design is based on the use of a new extended GAS canister and a low profile launch mechanism. The satellite is also configured to launch as a dedicated payload on SCOUT or commercial expendable launch vehicles. The satellite is cylindrical, measuring 19 inches in diameter and 35 inches long. The maximum spacecraft mass is 250 pounds, of which 32 pounds are nominally dedicated to user payloads. The remaining 218 pounds encompass the satellite structure and support elements, which include a hydrazine propulsion subsystem and a spin stabilized attitude control subsystem. The propulsion subsystem provides sufficient impulse to enable circular orbits as high as 835 nm or elliptic orbits with apogees at 2200 nm, leaving a nominal shuttle orbit of 135 nm. Four stabilizing booms or active nutation control techniques are employed for spin stabilization about the longitudinal axis of the spacecraft. Attitude control accuracies on the order of 1 deg are attainable for a total mission duration of 90 days to 3 years. Total satellite cost is $1.5 million. The thesis outlines the history of general purpose spacecraft, the ORION design criteria, and the design of the major subsystems

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Kramer, Alexander [Verfasser], Klaus [Gutachter] Schilling, Sergio [Gutachter] Montenegro, Georg [Gutachter] Herdrich, and Martin [Gutachter] Tajmar. "Orbit control of a very small satellite using electric propulsion / Alexander Kramer ; Gutachter: Klaus Schilling, Sergio Montenegro, Georg Herdrich, Martin Tajmar." Würzburg : Universität Würzburg, 2021. http://d-nb.info/1239563884/34.

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Bulut, Jane. "Design and CFD analysis of the demonstrator aerospike engine for a small satellite launcher application." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Starting with a brief overview of thrust generation for launchers, this study focuses on the design process of the demonstrator aerospike engine, DEMOP-1, of the Pangea Aerospace's commercial grade engine and its flow field analysis. The primary goal of the study is to obtain the plug nozzle design delivers 30 kN thrust using cryogenic liquid oxygen (LOX) as the oxidizer and cryogenic liquid methane (LCH4) as the fuel, with the mixture ratio of 3.4. Design parameters considered as 30 bar of combustion chamber pressure (Po) and expansion ratio as 15 for an optimum expanded nozzle. On the basis of decided design characteristics, Angelino's method is used to design the nozzle contour through MATLAB. The flow field over the aerospike analyzed using commercial CFD program FLUENT for sea level, optimum expansion and vacuum conditions. Flow simulations are carried out for air (specific heat ratio, gamma= 1.4), and afterwards based on the obtained thrust values at each altitude for air, expected thrust values for the real propellant, LOX/LCH4 (specific heat ratio, gamma = 1.1664), are calculated. Finally, the study is concluded with the comparison of trend in thrust and specific impulse for conventional bell nozzle and aerospike. For the conventional bell engine the values obtained in commercial computational simulation of chemical rocket propulsion and combustion software RPA for bell nozzle with same characteristics with aerospike, Po = 30 bar and expansion ratio = 15, are taken as reference for sea level, optimum expansion level and vacuum condition performance. Due to its ability to adopt the altitude, aerospike delivers higher performance at the low altitudes with respect to the conventional bell nozzle which has the same expansion ratio and combustion chamber pressure. Last in order but not in importance, after obtaining the flow field on plug of the aerospike, the shock wave impingement on the nozzle surface at sea level has been investigated.

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Sunny, Ajin. "SINGLE-DEGREE-OF-FREEDOM EXPERIMENTS DEMONSTRATING ELECTROMAGNETIC FORMATION FLYING FOR SMALL SATELLITE SWARMS USING PIECEWISE-SINUSOIDAL CONTROLS." UKnowledge, 2019. https://uknowledge.uky.edu/me_etds/146.

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This thesis presents a decentralized electromagnetic formation flying (EMFF) control method using frequency-multiplexed sinusoidal control signals. We demonstrate the EMFF control approach in open-loop and closed-loop control experiments using a single-degree-of-freedom testbed with an electromagnetic actuation system (EAS). The EAS sense the relative position and velocity between satellites and implement a frequency-multiplexed sinusoidal control signal. We use a laser-rangefinder device to capture the relative position and an ARM-based microcontroller to implement the closed-loop control algorithm. We custom-design and build the EAS that implements the formation control in one dimension. The experimental results in this thesis demonstrate the feasibility of the decentralized formation control algorithm between two satellites.

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Hansel, George J. "Power conversion and scaling for vanishingly small satellites with electric propulsion." Thesis, Massachusetts Institute of Technology, 2014. http://hdl.handle.net/1721.1/90667.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2014.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 51-53).
The development of ion electrospray propulsion systems (iEPS) as integrated microelectromechanical systems (i.e. MEMS) effectively miniaturizes propulsion for nanosatellites. Current iEPS thrusters consist of arrays of ion emitters, with a thruster for CubeSat application consisting of hundreds of emitters on a 1 cm² package. As a consequence, the lower bound on the size of satellites incorporating ion-emitter thrusters is not generated by the size of the thrusters themselves but the power supply they require: approximately 1700 volts at hundreds of nanoamps per emitter; a region in parametric space that is poorly explored in terrestrial power converters. We discuss the design and construction of a high-boost-ratio hybrid switched-magnetic/switched-capacitor power supply capable of powering small emitter arrays or single-emitter electrospray propulsion systems. In particular, we discuss the effects of and component requirements necessary for scaling the converter to the size and weight required for a board-level-integrated femtosatellite incorporating several single-emitter thrusters for propulsion and attitude control. This comprises scaling effects for physical and component parameters within a converter topology (such as operating frequency, parasitic effects, and component mass), but also motivates the choice of converter topology, as some are sensitive and others robust to miniaturization.
by George J. Hansel.
S.M.

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Pahl, Ryan Alan. "Integration and test of a refrigerant-based cold-gas propulsion system for small satellites." Diss., Rolla, Mo. : Missouri University of Science and Technology, 2010. http://scholarsmine.mst.edu/thesis/pdf/Pahl_09007dcc8078c87e.pdf.

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Thesis (M.S.)--Missouri University of Science and Technology, 2010.
Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed April 21, 2010) Includes bibliographical references (p. 146-149).

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Sellers, Jerry Jon. "Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites." Thesis, University of Surrey, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.309201.

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Harper, James M. "Pocket Rocket: A 1U+ Propulsion System Design To Enhance CubeSat Capabilities." DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2218.

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The research presented provides an overview of a 1U+ form factor propulsion system design developed for the Cal Poly CubeSat Laboratory (CPCL). This design utilizes a Radiofrequency Electrothermal Thruster (RFET) called Pocket Rocket that can generate 9.30 m/s of delta-V with argon, and 20.2 ± 3 m/s of delta-V with xenon. Due to the demand for advanced mission capabilities in the CubeSat form factor, a need for micro-propulsion systems that can generate between 1 – 1500 m/s of delta-V are necessary. By 2019, Pocket Rocket had been developed to a Technology Readiness Level (TRL) of 5 and ground tested in a 1U CubeSat form factor that incorporated propellant storage, pressure regulation, RF power and thruster control, as well as two Pocket Rocket thrusters under vacuum, and showcased a thrust of 2.4 mN at a required 10 Wdc of power with Argon propellant. The design focused on ground testing of the thruster and did not incorporate all necessary components for operation of the thruster. Therefore in 2020, a 1U+ Propulsion Module that incorporates Pocket Rocket, the RF amplification PCB, a propellant tank, propellant regulation and delivery, as well as a DC-RF conversion with a PIB, that are all attached to a 2U customer CubeSat for a 3U+ overall form factor. This design was created to increase the TRL level of Pocket Rocket from 5 to 8 by demonstrating drag compensation in a 400 km orbit with a delta-V of 20 ± 3 m/s in the flight configuration. The 1U+ Propulsion Module design included interface and requirements definition, assembly instructions, Concept of Operations (ConOps), as well as structural and thermal analysis of the system. The 1U+ design enhances the capabilities of Pocket Rocket in a 1U+ form factor propulsion system and increases future mission capabilities as well as propulsion system heritage for the CPCL.

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Books on the topic "Small Satellite Propulsion"

1

Boyd, Austin Walker. Design considerations for the ORION satellite: Structure, propulsion and attitude control subsystems for a small, general purpose spacecraft. Monterey, California: Naval Postgraduate School, 1988.

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2

Small satellite propulsion options. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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3

Benefits of low-power electrothermal propulsion. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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4

M, Sankovic John, and United States. National Aeronautics and Space Administration., eds. Benefits of low-power electrothermal propulsion. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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M, Sankovic John, and United States. National Aeronautics and Space Administration., eds. Benefits of low-power electrothermal propulsion. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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M, Sankovic John, and United States. National Aeronautics and Space Administration., eds. Benefits of low-power electrothermal propulsion. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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7

Sellers, Jerry Jon. Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites. 1996.

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Investigation into Hybrid Rockets and Other Cost-Effective Propulsion System Options for Small Satellites. Storming Media, 1996.

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Book chapters on the topic "Small Satellite Propulsion"

1

Razzano, E., and M. Pastena. "A Novel AOCS Cold-Gas Micro-Propulsion System Design and Applications to Micro and Nano Satellites." In Small Satellite Missions for Earth Observation, 425–35. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-03501-2_40.

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2

Sellers, J. J., T. J. Lawrence, and M. Paul. "Results of Low-Cost Propulsion System Research for Small Satellite Application." In Embedded System Applications, 203–30. Boston, MA: Springer US, 1997. http://dx.doi.org/10.1007/978-1-4757-2574-2_15.

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3

Marcuccio, Salvo, Stefan Gregucci, and Pierpaolo Pergola. "Design Criteria of Remote Sensing Constellations of Small Satellites with Low Power Electric Propulsion and Distributed Payloads." In Proceedings of the 13th Reinventing Space Conference, 229–37. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-32817-1_20.

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Singh, Sukhmander, Sanjeev Kumar, Shravan Kumar Meena, and Sujit Kumar Saini. "Introduction to Plasma Based Propulsion System: Hall Thrusters." In Propulsion - New Perspectives and Applications [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.96916.

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Technically, there are two types of propulsion systems namely chemical and electric depending on the sources of the fuel. Electrostatic thrusters are used for launching small satellites in low earth orbit which are capable to provide thrust for long time intervals. These thrusters consume less fuel compared to chemical propulsion systems. Therefore for the cost reduction interests, space scientists are interested to develop thrusters based on electric propulsion technology. This chapter is intended to serve as a general overview of the technology of electric propulsion (EP) and its applications. Plasma based electric propulsion technology used for space missions with regard to the spacecraft station keeping, rephrasing and orbit topping applications. Typical thrusters have a lifespan of 10,000 h and produce thrust of 0.1–1 N. These devices have E→×B→ configurations which is used to confine electrons, increasing the electron residence time and allowing more ionization in the channel. Almost 2500 satellites have been launched into orbit till 2020. For example, the ESA SMART-1 mission (Small Mission for Advanced Research in Technology) used a Hall thruster to escape Earth orbit and reach the moon with a small satellite that weighed 367 kg. These satellites carrying small Hall thrusters for orbital corrections in space as thrust is needed to compensate for various ambient forces including atmospheric drag and radiation pressure. The chapter outlines the electric propulsion thruster systems and technologies and their shortcomings. Moreover, the current status of potential research to improve the electric propulsion systems for small satellite has been discussed.

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"SMALLSAT PROPULSION." In Small Satellites for Earth Observation, 319–28. De Gruyter, 2005. http://dx.doi.org/10.1515/9783110919806.319.

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Anis, Assad. "Cold Gas Propulsion System - An Ideal Choice for Remote Sensing Small Satellites." In Remote Sensing - Advanced Techniques and Platforms. InTech, 2012. http://dx.doi.org/10.5772/37149.

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Conference papers on the topic "Small Satellite Propulsion"

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Myers, Roger, Steven Oleson, and Francis Curran. "Small satellite electric propulsion options." In Intersociety Energy Conversion Engineering Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-4137.

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Djamal, Darfilal, Khatir Mohamed, and Alim Rustem Aslan. "RESISTOJET Propulsion System for Small Satellite." In 2019 9th International Conference on Recent Advances in Space Technologies (RAST). IEEE, 2019. http://dx.doi.org/10.1109/rast.2019.8767847.

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Zakirov, Vadim, David Gibbon, Martin Sweeting, Bob Reinicke, Ray Bzibziak, and Timothy Lawrence. "Specifics of small satellite propulsion. II." In 37th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3834.

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White, David, Stewart Bushman, John Schilling, Gregory Spanjers, Daron Bromaghim, Michael Dulligan, and James Lake. "AFRL MicroPPT Development for Small Satellite Propulsion." In 33rd Plasmadynamics and Lasers Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2120.

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Rhodes, Brandie L., and Paul D. Ronney. "Thermal Transpiration Applied to Small Satellite Propulsion." In AIAA Propulsion and Energy 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3813.

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Beckman, Emily A., and Steven H. Collicott. "Slosh in Small Satellite Conformal Tanks." In AIAA Propulsion and Energy 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3819.

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MEISSINGER, HANS. "A small, primary solar-electric propulsion demonstration satellite." In Space Programs and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1566.

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Keidar, Michael. "Micro-Cathode Arc Thruster for small satellite propulsion." In 2016 IEEE International Conference on Plasma Science (ICOPS). IEEE, 2016. http://dx.doi.org/10.1109/plasma.2016.7533973.

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Keidar, Michael. "Micro-Cathode Arc Thruster for Small Satellite Propulsion." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-0938.

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Keidar, Michael. "Micro-Cathode Arc Thruster for small satellite propulsion." In 2016 IEEE Aerospace Conference. IEEE, 2016. http://dx.doi.org/10.1109/aero.2016.7500506.

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Reports on the topic "Small Satellite Propulsion"

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Clauss, Craig W., Dennis L. Tilley, and David A. Barnhart. Benefits of Low-Power Stationary Plasma Thruster Propulsion for Small Satellites. Fort Belvoir, VA: Defense Technical Information Center, January 1995. http://dx.doi.org/10.21236/ada437488.

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