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        <title>Frontiers in Space Technologies | Space Propulsion section | New and Recent Articles</title>
        <link>https://www.frontiersin.org/journals/space-technologies/sections/space-propulsion</link>
        <description>RSS Feed for Space Propulsion section in the Frontiers in Space Technologies journal | New and Recent Articles</description>
        <language>en-us</language>
        <generator>Frontiers Feed Generator,version:1</generator>
        <pubDate>2026-05-11T06:11:34.225+00:00</pubDate>
        <ttl>60</ttl>
        <item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2023.1287474</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2023.1287474</link>
        <title><![CDATA[Modeling the influence of an electric thruster’s ion beam on its global EMC]]></title>
        <pubdate>2023-11-27T00:00:00Z</pubdate>
        <category>Methods</category>
        <author>Yannik Rover</author><author>Rainer Thueringer</author><author>Uwe Probst</author><author>Chris Volkmar</author>
        <description><![CDATA[This research deals with electromagnetic compatibility (EMC) in the field of electric propulsion (EP). To complete previous investigations, the emissions of a fully operating radio-frequency thruster (RIT)—including its extracted ion beam—were numerically analyzed. The ion beam was simulated and investigated with various characteristics. The simulations were performed by means of transient co-simulation. It is clear that the ion beam had a significant impact on the thruster emissions. Properties such as divergence angle and the conductivity of the beam, which can be directly attributed to the operating point of the plasma discharge inside the thruster, play a major role. The next steps will be to bring together all the knowledge gained about the emissions of the individual thruster components as well as the peripheral electronics.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2023.1191300</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2023.1191300</link>
        <title><![CDATA[The fission fragment rocket engine for Mars fast transit]]></title>
        <pubdate>2023-10-13T00:00:00Z</pubdate>
        <category>Perspective</category>
        <author>J. Gahl</author><author>A. K. Gillespie</author><author>R. V. Duncan</author><author>C. Lin</author>
        <description><![CDATA[In this paper we discuss the advantages and challenges of utilizing Fission Fragment Rocket Engines (FFREs) to dramatically reduce transit time in space travel, for example, traveling to Mars. We discuss methods to decrease the size and weight of FFREs. These include utilizing metallic deuterides as moderators, driving the engines with electron beam bremsstrahlung, and operating the FFREs as subcritical assemblies, not as nuclear reactors. We discuss these and other new innovations based upon improved materials and technology that may be integrated into a revolutionary nuclear rocket technology.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2023.1220011</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2023.1220011</link>
        <title><![CDATA[A comparison of Fourier and POD mode decomposition methods for high-speed Hall thruster video]]></title>
        <pubdate>2023-07-27T00:00:00Z</pubdate>
        <category>Methods</category>
        <author>J. W. Brooks</author><author>A. A. Kaptanoglu</author><author>M. S. McDonald</author>
        <description><![CDATA[Hall thrusters are susceptible to large-amplitude plasma oscillations that impact thruster performance and lifetime and are also difficult to model. High-speed cameras are a popular tool to study these dynamics due to their spatial resolution and are a popular, nonintrusive complement to in situ probes. High-speed video of thruster oscillations can be isolated (decomposed) into coherent structures (modes) with algorithms that help us better understand the evolution and interactions of each. This work provides an introduction, comparison, and step-by-step tutorial on established Fourier and newer Proper Orthogonal Decomposition (POD) algorithms as applied to high-speed video of the unshielded H6 6-kW laboratory model Hall thruster. From this dataset, both sets of algorithms identify and characterize m = 0 and m > 0 modes in the discharge channel and cathode regions of the thruster plume, as well as mode hopping between the m = 3 and m = 4 rotating spokes in the channel. The Fourier methods are ideal for characterizing linear modal structures and also provide intuitive dispersion relationships. By contrast, the POD method tailors a basis set using energy minimization techniques that better captures the nonlinear nature of these structures and with a simpler implementation. Together, the Fourier and POD methods provide a more complete toolkit for studying Hall thruster plasma instabilities and mode dynamics. Specifically, we recommend first applying POD to quickly identify the nature and location of global dynamics and then using Fourier methods to isolate dispersion plots and other wave-based physics.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2023.1103981</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2023.1103981</link>
        <title><![CDATA[Preliminary sizing and study of a hybrid rocket based combined cycle]]></title>
        <pubdate>2023-06-07T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Laurine Hillion</author><author>Jean-Denis Parisse</author><author>Alexandre Mangeot</author>
        <description><![CDATA[This study investigates the feasibility and performance of a missile propelled by a Hybrid Rocket-Based Combined Cycle (HRBCC) engine, which combines hybrid rocket and air-breathing engines. The HRBCC engine could enable intra and extra-atmospheric hypersonic flight in the future. Using a hybrid rocket engine could bring several advantages as reduced costs, increased reliability and simplicity. This research presents the unique feature of the hybrid rocket engine developed by HyPrSpace and explains its benefits for the conception of a HRBCC system. The performance of the missile was studied in two operational modes: pure rocket and ramjet. The results were then used to develop an in-house code that compared the trajectory of different missiles. Our findings indicate that HRBCC engines provide several advantages over other propulsive technologies and can meet the requirements of various military applications.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2023.1114188</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2023.1114188</link>
        <title><![CDATA[Micro-nozzle flow and thrust prediction with high-density ratio using DSMC selection limiter]]></title>
        <pubdate>2023-03-13T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>T. Frieler</author><author>R. Groll</author>
        <description><![CDATA[Introduction: A Direct Simulation Monte Carlo (DSMC) solver with a modified collisional routine is used to investigate an argon gas flow through a millimeter-scaled thruster nozzle with high-density ratios.Method: The limiter scheme, denoted as the constant selection limiter (CSL), limits the possible number of selected collisional pairs to a constant value in accordance with the present simulation particles in the cell.Results: Results of the CSL scheme are compared with the experimental and numerical results of a compressible Navier–Stokes solver and discussed in comparison with baseline DSMC simulations. The influence of collision limitation by the CSL is discussed on the stagnation pressure of the thruster and on thrust and specific impulse prediction. The application of the limiter scheme makes the prediction of stagnation pressure challenging in some cases.Discussion: In contrast, thrust and specific impulse are predicted well, and their study remains valid. Investigated mass flow rates are 0.178 mg/s ≤ṁ≤ 71.360 mg/s, and flow Knudsen numbers below Kn = 0.01 and over Kn = 10 are present. Near atmospheric conditions are reached inside the thruster, generating pressure ratios up to 3,741 along the nozzle. The computational performance of the scheme is also discussed, and speed-up factors up to 0.51 are achieved.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.1017442</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.1017442</link>
        <title><![CDATA[Dynamic soaring as a means to exceed the solar wind speed]]></title>
        <pubdate>2022-11-28T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Mathias N. Larrouturou</author><author>Andrew J. Higgins</author><author>Jeffrey K. Greason</author>
        <description><![CDATA[A technique by which a spacecraft can interact with flows of ionized gas in space (the solar wind or interstellar medium) in order to be accelerated to velocities greater than the flow velocity is explored. Inspired by the dynamic soaring maneuvers performed by sea birds and gliders in which differences in wind speed are exploited to gain velocity, in the proposed technique a lift-generating spacecraft circles between regions of the heliosphere that have different wind speeds, gaining energy in the process without the use of propellant and only modest onboard power requirements. In the simplest analysis, the spacecraft motion can be modeled as a series of elastic collisions between regions of the medium moving at different speeds. More detailed models of the spacecraft trajectory are developed to predict the potential velocity gains and the maximum velocity that may be achieved in terms of the lift-to-drag ratio of the vehicle. A lift-generating mechanism is proposed in which power is extracted from the flow over the vehicle in the flight direction and then used to accelerate the surrounding medium in the transverse direction, generating lift (i.e., a force perpendicular to the flow). Large values of lift-to-drag ratio are shown to be possible in the case where a small transverse velocity is imparted over a large area of interaction. The requirement for a large interaction area in the extremely low density of the heliosphere precludes the use of a physical wing, but the use of plasma waves generated by a compact, directional antenna to impart momentum on the surrounding medium is feasible, with the excitation of R-waves, X-waves, Alfven waves, and magnetosonic waves appearing as promising candidates. A conceptual mission is defined in which dynamic soaring is performed on the termination shock of the heliosphere, enabling a spacecraft to reach speeds approaching 2% of c within two and a half years of launch without the expenditure of propellant. The technique may comprise the first stage for a multistage mission to achieve true interstellar flight to other solar systems.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.1063163</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.1063163</link>
        <title><![CDATA[Editorial: Astrodynamics, guidance, navigation and control in chaotic multi-body environments]]></title>
        <pubdate>2022-10-26T00:00:00Z</pubdate>
        <category>Editorial</category>
        <author>Andrea Colagrossi</author><author>Stéphanie Lizy-Destrez</author><author>Nicola Baresi</author><author>Josep Masdemont</author><author>Lorenzo Bucci</author>
        <description></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.929179</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.929179</link>
        <title><![CDATA[Dynamics and control analysis during rendezvous in non-Keplerian Earth—Moon orbits]]></title>
        <pubdate>2022-10-17T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Mario Innocenti</author><author>Giordana Bucchioni</author><author>Giovanni Franzini</author><author>Michele Galullo</author><author>Fabio D’ Onofrio</author><author>Alexander Cropp</author><author>Massimo Casasco</author>
        <description><![CDATA[The paper describes the development of a framework capable of addressing some fundamental issues in the analysis of proximity operations between two spacecraft that are operating within a three-body model defined by two primaries and the spacecraft themselves. The main objective is to enable the capability of analysing dynamic and control issues during an automated rendezvous between a vehicle and a passive space station orbiting around the Earth - Moon L2 Lagrangian point on a near rectilinear halo orbit. The paper presents first a restricted three body model dynamics and a nominal approach trajectory, followed by an analysis of the influence of assumed actuators and sensors. Critical aspects such as selected failures are investigated, in order to ensure passive safety of the mission using impulsive maneuvers. An example of closed loop guidance in the near range is also presented and the overall performance are validated with an Ephemeris model available in the literature.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.920456</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.920456</link>
        <title><![CDATA[Double Tisserand graphs for low-energy lunar transfer design]]></title>
        <pubdate>2022-09-30T16:25:06.477Z</pubdate>
        <category>Methods</category>
        <author>Waldemar Martens</author><author>Lorenzo Bucci</author>
        <description><![CDATA[Tisserand graphs are a widespread tool for interplanetary trajectory and Moon tour design. They are based on the Jacobi constant being an integral of motion in the Circular Restricted Three Body Problem (CR3BP); as such, the classical Tisserand graph does not include the perturbation of bodies other than the flyby bodies. Low-energy transfers in the Earth-Moon system make use of the combined Earth, Moon, and Sun gravities, exploiting the third body perturbations to reach the Moon with a reduced transfer Δv. The paper, therefore, proposes a novel double Tisserand graph, where the level lines of both the Earth-Moon and the Sun-Earth CR3BPs are superimposed, portraying the complex 4-body dynamics into a single plot. Paths along such level lines correspond to trajectories utilizing the dynamical effect of the Moon or the Sun or a combination of both. We show how such a graph can be efficiently used for preliminary design of Weak Stability Boundary transfers, lunar resonance transfers, lunar flybys, weak lunar captures or any combination of them.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.919932</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.919932</link>
        <title><![CDATA[Formation flying along libration point orbits using chattering attenuation sliding mode control]]></title>
        <pubdate>2022-07-26T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Mai Bando</author><author>Hamidreza Namati</author><author>Yuki Akiyama</author><author>Shinji Hokamoto</author>
        <description><![CDATA[This paper studies a control law to achieve formation flying in cislunar space. Utilizing the eigenstructure of the linearized flow around a libration point of the Earth-Moon circular restricted three-body problem, the fuel efficient formation flying controller based on the chattering attenuation sliding mode controller is designed and analyzed. Numerical studies are conducted for the Earth-Moon L2 point and a halo orbit around it. The total velocity change required to achieve formation as well as to maintain the orbit is calculated. Simulation results show that the chattering attenuation sliding mode controller has good performance and robustness in the presence of unmodeled nonlinearity along the halo orbit with moderate fuel consumption.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2022.919311</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2022.919311</link>
        <title><![CDATA[Autonomous Crosslink Radionavigation for a Lunar CubeSat Mission]]></title>
        <pubdate>2022-06-29T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Erdem Turan</author><author>Stefano Speretta</author><author>Eberhard Gill</author>
        <description><![CDATA[This study presents an autonomous orbit determination system based on crosslink radiometric measurements applied to a future lunar CubeSat mission to clearly highlight its advantages with respect to existing ground-based navigation strategies. This work is based on the Linked Autonomous Interplanetary Satellite Orbit Navigation (LiAISON) method which provides an autonomous navigation solution solely using satellite-to-satellite measurements, such as range and/or range-rate, to estimate absolute spacecraft states when at least one of the involved spacecraft has an orbit with a unique size, shape, and orientation. The lunar vicinity is a perfect candidate for this type of application due to the asymmetrical gravity field: the selected lunar mission, an Earth-Moon L2 (EML2) Halo orbiter, has an inter-satellite link between a lunar elliptical frozen orbiter. Simulation results show that, even in case of high-measurement errors (in the order of 100 m, 1σ), the navigation filter estimates the true states of spacecraft at EML2 with an error in the order of 500 m for position, and 2 mm/s for velocity, respectively and the elliptical lunar frozen orbiter states can be estimated in the order of 100 m for position and 1 cm/s for velocity, respectively. This study shows that range-only measurements provide better state estimation than range-rate-only measurements for this specific situation. Different bias handling strategies are also investigated. It has been found that even a less accurate ranging method, such as data-aided ranging, provides a sufficient orbit determination solution. This would simplify the communication system design for the selected CubeSat mission. The most observable states are found to be position states of the lunar orbiter via the observability analysis. In addition, the best tracking windows are also investigated for the selected mission scenario.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2021.632358</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2021.632358</link>
        <title><![CDATA[Comparison of Submillinewton Thrust Measurements Between a Laser Interferometer and a Load Cell on a Pendulum Balance]]></title>
        <pubdate>2021-04-27T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Dimitrios Tsifakis</author><author>Christine Charles</author><author>Rod Boswell</author>
        <description><![CDATA[Reliable measurements of thrust from systems to be flown on satellites are essential to ensure repeatable maneuvering capability of small nanosatellites. Thrusters can be used to vary spacecraft orientation, detumbling, and orbit change. Tests have been conducted in a low-pressure vacuum system using a cold gas prototype thruster and two independently calibrated methods: a four-point pendulum with a laser interferometer displacement sensor and a load cell, both of which have measurement capabilities from tens of micronewtons to tens of millinewtons. The agreement is very good, lending confidence in both methods. The advantages and disadvantages of both methods will be discussed. They include absolute accuracy, low thrust accuracy, temporal resolution, simplicity of operation, cost, and sensitivity to vibrations generated by laboratory equipment such as pumps, fans, bumps, and human movement.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontiersin.org/articles/10.3389/frspt.2021.639819</guid>
        <link>https://www.frontiersin.org/articles/10.3389/frspt.2021.639819</link>
        <title><![CDATA[BepiColombo: A Platform for Improving Modeling of Electric Propulsion-Spacecraft Interactions]]></title>
        <pubdate>2021-03-11T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Félicien Filleul</author><author>Orson Sutherland</author><author>Fabrice Cipriani</author><author>Christine Charles</author>
        <description><![CDATA[This article provides the first results of a long-term study aimed at improving the validity of numerical modeling techniques for Electric Propulsion induced Spacecraft Charging using the Spacecraft Plasma Interaction System software. The preflight numerical model of the European Space Agency’s BepiColombo mission and its outputs are presented as a benchmark example of the present capabilities and limitations of the model. It is demonstrated that the code can obtain the spacecraft charging equilibrium by simulating the dynamic interactions between the electric propulsion system, the thruster-generated plasmas, and spacecraft systems exposed to space. The importance of including a physical description of the electron cooling in the freely expanding thruster plasmas is shown by comparing simulations with different polytropic indexes. It particularly highlights the inadequacy of treating the entire plasma as isothermal. The reported variability of the simulation outputs with numerical and physical parameters paves the way for future improvements in preflight design modeling and increased understanding of plasma thruster-induced charging processes through future comparison with available flight telemetries.]]></description>
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