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Готові списки джерел за темами / Gridded thruster

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Добірка наукової літератури з теми "Gridded thruster"

Автор: Grafiati

Опубліковано: 24 травня 2025

Оновлено: 31 травня 2025

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Статті в журналах з теми "Gridded thruster"

1

Yamashita, Yusuke, Ryudo Tsukizaki, Yuta Yamamoto, Daiki Koda, Kazutaka Nishiyama, and Hitoshi Kuninaka. "Azimuthal ion drift of a gridded ion thruster." Plasma Sources Science and Technology 27, no. 10 (October 16, 2018): 105006. http://dx.doi.org/10.1088/1361-6595/aae29b.

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2

Grondein, P., T. Lafleur, P. Chabert, and A. Aanesland. "Global model of an iodine gridded plasma thruster." Physics of Plasmas 23, no. 3 (March 2016): 033514. http://dx.doi.org/10.1063/1.4944882.

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3

Soulas, George C. "Modeling Neutral Densities Downstream of a Gridded Ion Thruster." Journal of Propulsion and Power 27, no. 3 (May 2011): 538–52. http://dx.doi.org/10.2514/1.b34094.

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4

Dobkevicius, Mantas, and Davar Feili. "Multiphysics Model for Radio-Frequency Gridded Ion Thruster Performance." Journal of Propulsion and Power 33, no. 4 (July 2017): 939–53. http://dx.doi.org/10.2514/1.b36182.

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5

Williams, Logan T., and Mitchell L. R. Walker. "Ion production cost of a gridded helicon ion thruster." Plasma Sources Science and Technology 22, no. 5 (September 27, 2013): 055019. http://dx.doi.org/10.1088/0963-0252/22/5/055019.

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6

Aanesland, Ane, Dmytro Rafalskyi, Jerome Bredin, Pascaline Grondein, Noureddine Oudini, Pascal Chabert, Dimitry Levko, Laurent Garrigues, and Gerardus Hagelaar. "The PEGASES Gridded Ion-Ion Thruster Performance and Predictions." IEEE Transactions on Plasma Science 43, no. 1 (January 2015): 321–26. http://dx.doi.org/10.1109/tps.2014.2369534.

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7

Magaldi, Bernardo, Júlia Karnopp, Argemiro da Silva Sobrinho, and Rodrigo Pessoa. "A Global Model Study of Plasma Chemistry and Propulsion Parameters of a Gridded Ion Thruster Using Argon as Propellant." Plasma 5, no. 3 (July 28, 2022): 324–40. http://dx.doi.org/10.3390/plasma5030025.

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Анотація:

This work reports on the (zero-dimensional) global model study of argon plasma chemistry for a cylindrical thruster based on inductively coupled plasma (ICP) whose output has a system of two grids polarized with each other with direct current potential. The global model developed is based on particle and energy balance equations, where the latter considers both charged and neutral species. Thus, the model allows the determination of the neutral gas temperature. Finally, this study also investigated the role of excited species in plasma chemistry especially in the ions production and its implications for propulsion parameters, such as thrust. For this, the study was carried out in two different scenarios: (1) one taking into account the metastable species Arr and Arp (multi-step ionization), and (2) the other without these species (single-step ionization). Results indicates a distinct behavior of electron temperature with radiofrequency (RF) power for the investigated cases. On the other hand, the gas temperature is almost the same for investigated power range of up to 900 W. Concern propulsion analysis, a thrust of 40 mN at 450 W was verified for case (1), which represents a remarkable thrust value for electric thrusters.

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8

Neumann, Andreas, and Nina Sarah Mühlich. "Ground-Based Experiment for Electric Propulsion Thruster Plume—Magnetic Field Interaction." Aerospace 10, no. 2 (January 26, 2023): 117. http://dx.doi.org/10.3390/aerospace10020117.

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Electric space propulsion is a technology which is employed on a continuously increasing number of spacecrafts. While the current focus of their application area is on telecommunication satellites and on space exploration missions, several new ideas are now discussed that go even further and apply the thruster plume particle flow for transferring momentum to targets such as space debris objects or even asteroids. In these potential scenarios, the thruster beam impacts on distant objects and subsequently generates changes in their flight path. One aspect which so far has not been systematically investigated is the interaction of the charged particles in the propulsion beam with magnetic fields which are present in space. This interaction may result in a deflection of the particle flow and consequently affect the aiming strategy. In the present article, basic considerations related to the interaction between electric propulsion thruster plumes and magnetic fields are presented. Experiments with respect to these questions were conducted in the high-vacuum plume test facility for electric thrusters (STG-ET) of the German Aerospace Center in Göttingen utilizing a gridded ion thruster, an RIT10/37, and a Helmholtz coil to generate magnetic fields of varying field strength. It was possible to detect a beam deflection on the RIT ion beam caused by a magnetic field with an Earth-like magnetic field strength.

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9

Williams, Logan T., and Mitchell L. R. Walker. "Initial Performance Evaluation of a Gridded Radio Frequency Ion Thruster." Journal of Propulsion and Power 30, no. 3 (May 2014): 645–55. http://dx.doi.org/10.2514/1.b35018.

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10

Rovey, Joshua L., and Alec D. Gallimore. "Dormant Cathode Erosion in a Multiple-Cathode Gridded Ion Thruster." Journal of Propulsion and Power 24, no. 6 (November 2008): 1361–68. http://dx.doi.org/10.2514/1.37031.

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Більше джерел

Дисертації з теми "Gridded thruster"

1

Kindberg, Peter. "Development of a miniature Gridded ion thruster." Thesis, Luleå tekniska universitet, Rymdteknik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-65750.

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2

Lequette, Nicolas. "Numerical model of the PEGASES spacecraft thruster." Electronic Thesis or Diss., Institut polytechnique de Paris, 2025. http://www.theses.fr/2025IPPAX037.

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Анотація:

L'industrie de la propulsion spatial électrique est en train de transitionner vers de nouveaux ergols.Jusqu'à récemment, le xénon était privilégié. Il s'agit du plus lourd des gaz nobles stable, caractéristiques qui bénéficient au rapport poussée/puissance des propulseurs électriques.Cependant, l'offre limitée ne peut satisfaire la demande croissante à mesure que l'espace s'industrialise.De nouveaux systèmes de propulsion sont conçus autour de gaz nobles plus légers, sacrifiant l'efficacité pour le prix. D'autres utilisent des ergols moléculaires, notamment l'iode.Bien que réactif, cet élément voisin du xénon dans le tableau périodique peut offrir des performances similaires avec l'avantage d'une plus grande densité de stockage.Le développement des prochains systèmes de propulsion nécessite des outils de conception et de simulation adaptés aux ergols alternatifs. Dans ce travail, nous proposons d'utiliser un code 1D Particle-In-Cell couplé à un modèle de fluide comme moyen rapide de simuler les décharges à basse pression que l'on trouve dans les moteurs électriques. Nous avons mis en œuvre un modèle analytique pour émuler le transport des particules dans les directions non simulées.Cette méthode permet de simuler des géométries simples avec un modèle 1D. En outre, la technique de changement d'échelle de la permittivité du vide permet de simuler rapidement des systèmes complets.Pour garantir la précision de notre modèle, nous l'avons validé de manière approfondie en utilisant les diagnostic mesurées sur le propulseur PEGASES. Ce processus de validation a couvert des décharges inductives avec de l'iode et divers gaz nobles, l'argon, le krypton et le xénon.La validation des gaz rares a montré que le code pouvait reproduire les tendances des variations des paramètres électroniques au fur et à mesure de l'évolution de la pression et de la puissance.Cependant, sa dimensionnalité réduite et le modèle fluide, entravent son pouvoir prédictif aux plus basses pressions et a trop haute puissance. Pour l'iode, les simulations à basse pression sont en bon accord avec les données expérimentales. Cependant, le modèle peine à maintenir l'équilibre délicat entre les nombreuses espèces à haute pression
The electric spacecraft propulsion industry is actively transitioning to new propellants.Until recently, the favoured propellant was xenon. It is the heaviest stable noble gas, characteristics that enhance the thrust-to-power ratio of electric thrusters. However, the limited supply cannot satisfy the growing demand as space industrializes.New propulsion systems are designed around lighter noble gases, trading efficiency for affordability.Others make use of molecular propellants, namely iodine. Despite being reactive, this element, a neighbour of xenon in the periodic table, can offer similar performances with the benefit of a higher storage density.The development of the next propulsion systems requires design and simulation tools adapted to alternative propellants. In this work, we propose using a 1D Particle-In-Cell code coupled with a fluid model as a fast way to simulate the low-pressure discharges found in electric thrusters.We implemented an analytical model to emulate the particle transport in the unsimulated directions.This method allows the simulation of simple geometries with a 1D model. In addition, the vacuum permittivity scaling technique allows to speed up whole device simulations.To ensure the accuracy of our model, we extensively validated it using the diagnostic data measured on the PEGASES thruster. This validation process covered a range of noble gases and iodine ICP discharges, including argon, krypton, xenon.Noble gas validation showed that the code could reproduce the trends in the electron parameters as the pressure and power evolved. However, its reduced dimensionality and the fluid model hinder its predictive power at low pressure and high power. In iodine, the low-pressure simulations are in good agreement with the experimental data. However, the model struggles to maintain the delicate balance between the numerous species at high pressure

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3

Bek, Jeremy. "Design, simulation, and testing of an electric propulsion cluster frame." Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-300970.

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Анотація:

In general, electric propulsion oﬀers very high eﬃciency but relatively low thrust. To remedy this, several ion engines can be assembled in a clustered conﬁguration and operated in parallel. This requires the careful design of a frame to accommodate the individual propulsion systems. This frame must be modular to be used in diﬀerent cluster sizes, and verify thermal and mechanical requirements to ensure the nominal operation of the thrusters. The present report aims to show the design process of such a frame, from preliminary modelling to the experimental study of a prototype. This document features an overview of the iterative design process driven by thermal simulations rendered on COMSOL Multiphysics. This process led to the conception of a 2-thruster and 4-thruster cluster frame. A lumped-parameter model of the electric propulsion system was also created to model its complex thermal behaviour. In addition, the 2-thruster frame was studied mechanically with analytical calculations and simulations of simple load cases on SolidWorks. Lastly, a prototype based on the 2-thruster frame model was assembled. The prototype was used to conduct temperature measurements while hosting two operating thrusters inside a vacuum chamber. The temperature distribution in the cluster was measured, and compared to simulation results. Thermal simulations of the 2-thruster and 4-thruster frame showed promising results, while mechanical simulations of the 2-thruster version met all requirements. Moreover, experimental results largely agreed with thermal simulations of the prototype. Finally, the lumped-element model proved instrumental in calibrating the models, with its high ﬂexibility and quick computation time.
Generellt erbjuder elektrisk framdrivning hög verkningsgrad men relativt låg dragkraft. För att avhjälpa detta kan ﬂera jonmotorer sättas samman i en klusterkonﬁguration och drivs parallellt. Detta kräver en noggrann utformning av en ram för att rymma de enskilda framdrivningssystemen. Denna ram måste vara modulär för att kunna användas i olika klusterstorlekar och veriﬁera termiska och mekaniska krav för att säkerställa den nominella driften av motorerna. Föreliggande rapport syftar till att visa designprocessen för en sådan ram, från preliminär modellering till experimentell studie av en prototyp. Detta dokument innehåller en översikt över den iterativa designprocessen, driven av termiska simuleringar gjorda med COMSOL Multiphysics, som ledde till uppfattningen av en 2 motorer och 4 motorer ram. En klumpelementmodell av jonmotorn skapades också för att modellera dess komplexa termiska beteende. Dessutom var den 2 motorer ram studeras mekaniskt med analytiska beräkningar och simuleringar av enkla laddafall med SolidWorks. Slutligen monterades en prototyp baserad på den 2 motorer rammodellen. Prototypen användes för att göra temperaturmätningar medan den är värd för 2 jonmotorer i en vakuumkammare. Temperaturfördelningen i klustret mättes och jämfördes med simuleringsresultat. Termiska simuleringar av den 2 motorer och 4 motorer ramen visade lovande resultat, medan mekaniska simuleringar av den 2 motorer versionen klarade alla krav. Dessutom överensstämde experimentella resultat till stor del med termiska simuleringar av prototypen. Slutligen var klumpelementmodellen mycket användbar för att kalibrera de andra modellerna med sin höga ﬂexibilitet och snabba beräkningstid.

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4

Dobkevicius, Mantas. "Modelling and design of inductively coupled radio frequency gridded ion thrusters with an application to Ion Beam Shepherd type space missions." Thesis, University of Southampton, 2017. https://eprints.soton.ac.uk/413768/.

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Recently proposed space missions such as Darwin, LISA and NGGM have encouraged the development of electric propulsion thrusters capable of operating in the micro-Newton (N) thrust range. To meet these requirements, radio frequency (RF) gridded ion thrusters need to be scaled down to a few centimetres in size. Due to the small size of these thrusters, it is important to accurately determine the thermal and performance parameters. To achieve this, an RF ion thruster model has been developed, composed of plasma discharge, 2D axisymmetric ion extraction, 3D electromagnetic, 3D thermal and RF circuit models. The plasma discharge model itself is represented using 0D global, 2D axisymmetric and 3D molecular neutral gas, and Boltzmann electron transport sub-models. This is the rst time such a holistic/comprehensive model has been created. The model was successfully validated against experimental data from the RIT 3.5 thruster, developed for the NGGM mission. Afterwards, the computational model was used to design an RF gridded ion thruster for an Ion Beam Shepherd (IBS) type space debris removal mission. Normally, the IBS method requires two thrusters: one for impulse transfer (IT) and one for impulse compensation (IC). This thesis proposes a novel thruster concept for the IBS type missions where a single Double-Sided Thruster (DST) simultaneously producing ion beams for the IT and IC purposes is used. The advantage of DST design is that it requires approximately half the RF power compared with two single-ended thrusters and it has a much simpler sub-system architecture, lower cost, and lower total mass. Such a DST thruster was designed, built and tested, with the requirements and constraints taken from the LEOSWEEP space debris removal mission. During the experimental campaign, a successful extraction of two ion beams was achieved. The thesis has shown that it is possible to control the thrust magnitudes from the IT and IC sides by varying the number of apertures in each ion optics system, proving that the DST concept is a viable alternative for the LOESWEEP mission.

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Тези доповідей конференцій з теми "Gridded thruster"

1

Lettera, Elpidio, Lucia Mazza, Valeria Sangiacomo, Elisa Rosella, Federica Ciccarelli, Sharon Frattolillo, Maria Fricchione, et al. "Preliminary Design for Air-Breathing Gridded Ion Thruster." In IAF Space Propulsion Symposium, Held at the 75th International Astronautical Congress (IAC 2024), 2002–17. Paris, France: International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078371-0220.

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2

Rafalskyi, Dmytro, and Ane Aanesland. "Neutralizer-free gridded ion thruster." In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-3423.

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3

Crandall, Patrick, Christopher Cretel, and Richard E. Wirz. "RF Gridded Ion Thruster Design for Laboratory Experiments." In AIAA SCITECH 2024 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2024. http://dx.doi.org/10.2514/6.2024-1549.

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4

Soulas, George. "Modeling Neutral Densities Downstream of a Gridded Ion Thruster." In 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-6699.

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5

Yamauchi, Toyofumi, and Kunning G. Xu. "A Miniature Gridded Ion Thruster using Split Ring Resonator Microplasma." In 2018 Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4651.

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6

Tompkins, Joshua, Richeek Dutta, and Joshua L. Rovey. "Plasma Hysteresis of Alternative Propellants in ECR Gridded Ion Thruster." In AIAA SCITECH 2024 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2024. http://dx.doi.org/10.2514/6.2024-1546.

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7

Dankanich, John, and Tara Polsgrove. "Mission Benefits of Gridded Ion and Hall Thruster Hybrid Propulsion Systems." In 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-5162.

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8

Mishra, Ishaan, Timothy Ausec, H. Onur Dorduncu, Adam Jirovec, Justin Lin, Miguel Vasquez, and Ben Mertz. "Development of an Undergraduate DC-Discharge Ring-Cusp Miniature Gridded Ion Thruster." In 2024 IEEE Aerospace Conference. IEEE, 2024. http://dx.doi.org/10.1109/aero58975.2024.10521066.

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9

Martínez, Miguel Astudillo, Guillermo Núñez Rodriguez, Javier Torres Cabanuz, Regina Ramos Hortal, and Pedro Alou Cervera. "Analysis and Design of a Radio Frequency Generator for Gridded Ion Technology Thruster." In 2023 13th European Space Power Conference (ESPC). IEEE, 2023. http://dx.doi.org/10.1109/espc59009.2023.10298181.

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10

Nishii, K., and D. Levin. "Fully Kinetic PIC Simulations of the Electrical Facility Effect on the Gridded Ion Thruster Testing." In 2023 IEEE International Conference on Plasma Science (ICOPS). IEEE, 2023. http://dx.doi.org/10.1109/icops45740.2023.10481012.

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