Acta Astronautica最新文献

{"title":"Analysis of satellite attitude motion in a three-body tethered system during deployment via integral manifolds","authors":"Ying Zhang ,&nbsp;Changqing Wang ,&nbsp;Yuriy Zabolotnov ,&nbsp;Aijun Li ,&nbsp;Hongshi Lu","doi":"10.1016/j.actaastro.2024.10.062","DOIUrl":"10.1016/j.actaastro.2024.10.062","url":null,"abstract":"<div><div>This paper aims to analyze the impact of unideal end-body configurations on attitude motion during the tether deployment process in a linear three-body tethered system (LTBTS). A main challenge in this process is the resonance between the nutation and spin angles caused by the unideal end-body configurations, leading to severe nutation angle oscillations. These oscillations can result in tether entanglement with the end-bodies or even tether rupture. To address this issue, the deployment model for the LTBTS is first established using the Lagrangian equations, with the end-body attitude described by Eulerian angles. Secondly, the system involves the separation of two subsatellites from the central main satellite in opposite directions. The dynamics response of the deployment process under unideal configuration of end-bodies is investigated. Resonance phenomena in nutation and spin angles are observed due to errors in initial angles/angular velocities, offset errors of tether connection points, and unideal structural characteristics of the satellites. Thirdly, to further understand this resonance, analytical solutions for resonance are derived by transforming the nutation angle equations, and satellite attitude equations are systematically solved via integral manifold methods. Potential resonance issues are mitigated by reducing system asymmetry and minimizing initial disturbances. Finally, the effectiveness of the dynamic analysis is validated through simulations.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 716-727"},"PeriodicalIF":3.1,"publicationDate":"2024-11-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142661037","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Experimental study on droplet dynamics behavior and combustion characteristics of high performance green propellant in electrical ignition mode","authors":"JinZe Wu ,&nbsp;GuoXiu Li ,&nbsp;HongMeng Li ,&nbsp;Shuo Zhang ,&nbsp;ZhaoPu Yao ,&nbsp;Tao Zhang","doi":"10.1016/j.actaastro.2024.11.003","DOIUrl":"10.1016/j.actaastro.2024.11.003","url":null,"abstract":"<div><div>High performance green propellant represented by ammonium dinitramide-based liquid propellant and its new ignition method are the research hotspots of space propulsion in the 21st century. Exploring the complex multi-scale physical properties of multi-component ammonium dinitramide-based liquid propellant droplets in the electrical ignition mode has wide application significance for spray, propulsion system design and combustion control. The droplet dynamics behavior and combustion characteristics of propellant droplets at different ignition voltages were studied experimentally. The droplet dynamics behavior during the evaporation process, including violent volume oscillation, approximate steady-state expansion, contraction, secondary expansion, puffing and micro-explosion, have been determined by the generation, growth, and discharge of vapor bubbles. In the initial evaporation process, the heterogeneous nucleation is dominant. As the droplet is continuously heated, homogenization nucleation gradually dominates. The main physical and chemical mechanisms of bubble evolution driven by temperature involve methanol boiling, water overheating, ammonium dinitramide decomposition and combustion reaction between vapor molecules. Increasing the ignition voltage increases the droplet dynamics behavior and the combustion, but promotes the combustion instability. Increasing the ignition voltage increases the ignition delay time, puffing delay time, droplet lifetime, maximum temperature of droplet, and reduces the ignition critical diameter. It is proposed that the method of suppressing the droplet breakup dynamics at decomposition area and enhancing the droplet breakup dynamics at the combustion area are conducive to the combustion control of the thruster in electrical ignition mode. This research provides novel insight into the study of the electrical ignition mechanism of liquid fuels.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 653-668"},"PeriodicalIF":3.1,"publicationDate":"2024-11-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142660955","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"The additionally charged forces in the Sun-Earth and Earth-Moon systems","authors":"Ting-Han Pei","doi":"10.1016/j.actaastro.2024.10.072","DOIUrl":"10.1016/j.actaastro.2024.10.072","url":null,"abstract":"<div><div>We build a model to describe the net charges existing in the Sun and Earth. According to statistical mechanics, electrons on average move much faster than protons and neutrons at the same temperature. Electrons escape the Sun more easily than protons and neutrons, so the Sun becomes a charged star. We estimate the maximal net charges in the Sun by using statistical mechanics first. Then, we analyze the dynamical cycles between the positive and negative charged states. At a distance far away from the Sun, the effective net charges including the leaving protons and electrons are about <span><math><mrow><mn>6.3</mn><mo>×</mo><msup><mn>10</mn><mn>9</mn></msup><mspace></mspace><mi>C</mi></mrow></math></span> with energies of 1 GeV initially. We also use another way based on the observations of the Earth's perihelion precession to estimate the minimum and maximum net charges between <span><math><mrow><mn>1.15</mn><mo>×</mo><msup><mn>10</mn><mn>8</mn></msup><mspace></mspace><mi>C</mi></mrow></math></span> and <span><math><mrow><mn>2.80</mn><mo>×</mo><msup><mn>10</mn><mn>10</mn></msup><mspace></mspace><mi>C</mi></mrow></math></span> in space from the Sun to Earth. The most charged particles from the Sun to the Earth are electrons, so both the Moon and Earth are impacted by them and very possibly have the same electricity. Next, we propose new physical mechanisms causing the slowdown of the Earth's spin and propose Coulomb's repulsive force resulting in the increasing distance between the Moon and Earth. As a result, it gives the net charges of <span><math><mrow><mn>1.11</mn><mo>×</mo><msup><mn>10</mn><mn>6</mn></msup><mspace></mspace><mi>C</mi></mrow></math></span> surrounding the Earth and <span><math><mrow><mn>8.29</mn><mo>×</mo><msup><mn>10</mn><mn>3</mn></msup><mspace></mspace><mi>C</mi></mrow></math></span> surrounding the Moon. Our estimations also correspond to early works. The charges surrounding the Sun and Earth cause the Earth to be long-term accelerated in the radial direction by Coulomb's force. Finally, using the effective net charges of the Sun and Earth, we calculate the increasing distance between 11.4 <em>m</em> and 19.4 <em>m</em> on average per century if the initial radial velocities of the Earth are in between <span><math><mrow><mn>3.59</mn><mo>×</mo><msup><mn>10</mn><mrow><mo>−</mo><mn>9</mn></mrow></msup><mspace></mspace><mi>m</mi><mo>/</mo><mi>s</mi></mrow></math></span> and <span><math><mrow><mn>6.12</mn><mo>×</mo><msup><mn>10</mn><mrow><mo>−</mo><mn>9</mn></mrow></msup><mspace></mspace><mi>m</mi><mo>/</mo><mi>s</mi></mrow></math></span>, which satisfies the observed reports.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 555-569"},"PeriodicalIF":3.1,"publicationDate":"2024-11-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142593299","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Effect of input power on plasma expansion and ion acceleration in a radio-frequency plasma thruster","authors":"Antonella Caldarelli ,&nbsp;Raoul Andriulli ,&nbsp;Fabrizio Ponti ,&nbsp;John Cater ,&nbsp;Nicholas Rattenbury","doi":"10.1016/j.actaastro.2024.10.055","DOIUrl":"10.1016/j.actaastro.2024.10.055","url":null,"abstract":"<div><div>Exploring the physics of low pressure plasmas expanding in a diverging magnetic nozzle, and the resulting acceleration mechanisms, plays an important role in the development of a new-type of electrode-less plasma propulsion systems. This study discusses the effects of input power on plasma expansion and ion beam acceleration in a magnetic nozzle electrode-less plasma thruster. The experiments were conducted in a radio-frequency magnetic nozzle plasma device at The University of Auckland with four different power configurations <span><math><msub><mrow><mi>P</mi></mrow><mrow><mi>RF</mi></mrow></msub></math></span>. Different plasma diagnostics were used to measure the characteristics of the plasma plume. A planar Langmuir probe was used to measure the floating potential and ion saturation current both in the plasma source and in the expansion chamber. The potential drop in the plasma source was obtained with an emissive probe. A retarding field energy analyser was employed to evaluate the local plasma and ion beam potentials, the ion energy distribution functions, and to estimate the ion beam speed in the expansion region. Measurements showed that, as expected, increasing the power input resulted in a higher plasma and supersonic ion density, while the ion beam speed did not increase further for <span><math><mrow><msub><mrow><mi>P</mi></mrow><mrow><mi>RF</mi></mrow></msub><mo>&gt;</mo><mn>100</mn></mrow></math></span> <!--> <!-->W. Interestingly, and contrary to the idealised physical model, the ion sonic transition did not occur at the magnetic nozzle throat, but instead close to the geometrical expansion point, i.e. near the interface between the source tube and the expansion chamber. This feature would result in a lower performance of the thruster given the reduced expansion ratio. An E-H mode change is also observed to occur in the device with increasing radio-frequency power that would help explain the different plasma characteristics observed at the 200<!--> <!-->W transition point.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 521-530"},"PeriodicalIF":3.1,"publicationDate":"2024-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142593297","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Intelligent control algorithms to ensure the flight safety of aerospace vehicles","authors":"S. Chernyshev ,&nbsp;K. Sypalo ,&nbsp;S. Bazhenov","doi":"10.1016/j.actaastro.2024.10.073","DOIUrl":"10.1016/j.actaastro.2024.10.073","url":null,"abstract":"<div><div>An overview of the architectures, functions and algorithms of aircraft-type aerospace vehicles equipped with fly-by-wire (FBW) digital integrated control systems (ICS) is given. The ICS has a hierarchical architecture, including the primary, backup and emergency control systems with a sophisticated control reconfiguration logic in the event of failures. Digital control computers have dissimilar redundancy of equipment and software. At the atmospheric flight stage, integrator control laws provide the specified control characteristics, flight envelope protection, automatic trim of vehicle and crew workload alleviation. Further integration of manual and automatic control, implementation of the control philosophy as a continuation of the pilot's actions, more intellectual control system and human-machine interface, use of multiple control surfaces to ensure optimal vehicle configuration and alleviate structural loading together with basic control functions are considered as promising areas for ICS improvement.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 782-790"},"PeriodicalIF":3.1,"publicationDate":"2024-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142661040","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Effects of pulse injection on the flow field structure and combustion performance in a kerosene-fueled supersonic combustor","authors":"Chen Chen ,&nbsp;Yunfei Wang ,&nbsp;Ye Tian ,&nbsp;Weixin Deng","doi":"10.1016/j.actaastro.2024.10.071","DOIUrl":"10.1016/j.actaastro.2024.10.071","url":null,"abstract":"<div><div>This paper describes the pulse injection of kerosene fuel in a kerosene-fueled supersonic combustor at a Mach number of 3. A high-flow mechanical pulsed injector was utilized to inject kerosene at frequencies ranging from 40 to 212 Hz in experiments. High-speed Schlieren images and wall pressure were employed to analyze the influences of various injection frequencies on the wave family and kerosene combustion performance. Initially, the pulsed injection causes intermittent changes in the wave family after kerosene ignition, leading to combustion instability. However, an optimal injection frequency of 143 Hz stabilizes the wave family. Additionally, pulsed injection reduces the kerosene ignition delay time, with the most notable reduction occurring at 113 Hz. Finally, the average combustion intensity of kerosene with pulse injection is lower than that of steady injection. However, the instantaneous combustion intensity at 143 Hz is similar to steady injection, which constitutes a significant portion of the overall combustion process. In summary, pulse injection of kerosene at 143 Hz could achieve efficient and stable combustion at a Mach number of 3.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 479-493"},"PeriodicalIF":3.1,"publicationDate":"2024-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142587325","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Evaluating potential landing sites for the Artemis III mission using a multi-criteria decision making approach","authors":"Eloy Peña-Asensio ,&nbsp;Álvaro-Steve Neira-Acosta ,&nbsp;Juan Miguel Sánchez-Lozano","doi":"10.1016/j.actaastro.2024.10.049","DOIUrl":"10.1016/j.actaastro.2024.10.049","url":null,"abstract":"<div><div>The selection of a landing site within the Artemis Exploration Zone (AEZ) involves multiple factors and presents a complex problem. This study evaluates potential landing sites for the Artemis III mission using a combination of Geographic Information Systems (GIS) and Multi-Criteria Decision Making (MCDM) methodologies, specifically the TOPSIS algorithm. By integrating topographic, illumination, and mineralogy data of the Moon, we assess 1247 locations that meet the Human Landing System (HLS) requirements within 13 candidate regions and Site 004 near the lunar south pole. Criteria considered include surface visibility, HLS-astronaut line of sight, Permanently Shadowed Regions (PSRs), sunlight exposure, direct communication with Earth, geological units, and mafic mineral abundance. Site DM2 (Nobile Rim 2), particularly the point at latitude 84°12’5.61”S (−84.20156°) and longitude 60°41’59.61”E (60.69989°), is the optimal location for landing. Sensitivity analysis confirms the robustness of our approach, validating the suitability of the best location despite the MCDM method employed and variations in criteria weightings to prioritize illumination and PSRs. This research demonstrates the applicability of GIS-MCDM techniques for lunar exploration and the potential benefits they can bring to the Artemis program.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 469-478"},"PeriodicalIF":3.1,"publicationDate":"2024-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142578641","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Satellite surface charging in LEO with ProPIC","authors":"Simone Di Fede ,&nbsp;Basman Elhadidi ,&nbsp;Mirko Magarotto ,&nbsp;Wai Lee Chan","doi":"10.1016/j.actaastro.2024.10.057","DOIUrl":"10.1016/j.actaastro.2024.10.057","url":null,"abstract":"<div><div>ProPIC is a fully kinetic particle-in-cell (PIC) solver developed for space electric propulsion. This work has extended its capabilities to simulate satellite surface charging and wake generation in low Earth orbit (LEO). A novel scaling approach has been implemented, decreasing computational cost by more than one order of magnitude. The methodology and scaling approach have been verified against the revised orbital-motion-limited theory. The surface charging and wake generation in LEO have been examined for a satellite that is more complex and larger than what is typically handled with a fully kinetic PIC approach in LEO, particularly due to the presence of large solar panels. Notably, the simulated wake can be used to identify the optimal position for the plasma diagnostic sensor that minimizes interference with the wake. Moreover, despite not being a failure risk, the attitude greatly influences the surface charging of a satellite with large solar arrays installed parallel to the satellite speed vector. The study suggests that, for high positive pitch angles (<span><math><mo>&gt;</mo></math></span>45<span><math><msup><mrow></mrow><mrow><mo>∘</mo></mrow></msup></math></span>), the surface charging of the solar panels can increase by as much as 75% compared to low negative pitching cases. Additionally, the study highlights that the pitch angle and satellite envelope along the motion direction significantly influence the potential gradients on the solar panels.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 458-468"},"PeriodicalIF":3.1,"publicationDate":"2024-10-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142578640","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Martian buildings: Feasible cement/concrete for onsite sustainable construction from the structural point of view","authors":"Omid Karimzade Soureshjani,&nbsp;Ali Massumi,&nbsp;Gholamreza Nouri","doi":"10.1016/j.actaastro.2024.10.056","DOIUrl":"10.1016/j.actaastro.2024.10.056","url":null,"abstract":"<div><div>Colonizing other planets, like Mars, marks a significant milestone in the pursuit of a multi-planetary existence. Millions of people would settle on Mars in self-sufficient bases. Colonizing Mars is a long-term mission that demands self-sufficient, secure habitats and comprehensive planning. Importing structures, such as inflatable structures, from Earth is cost-prohibitive, making the utilization of in-situ resources and onsite construction the most viable approach for preparing the required buildings. Studies have shown that it is possible to produce and craft several kinds of binders and concretes with appropriate mechanical behavior using Martian soil composition; however, determining the optimal option for onsite construction remains a challenge. This study investigates available cement/concrete options for onsite construction on Mars from a structural engineering perspective, taking into account the available resources and technologies. In this regard, the observations and data provided by Martian landers, rovers, orbiters and methods such as Viking-1 &amp; 2, Pathfinder, Spirit, Opportunity, Curiosity, Mars Express, Ultraviolet–visible/Near-infrared reflectivity spectra and Alpha particle X-ray spectrometer were used to obtain a comprehensive and detailed investigation. Eleven types of Martian cement/concrete based on the in-situ resources, soil composition, and available technologies were compared based on the criteria and indices defined in accordance with the structural engineering point of view to select the best practical option for onsite construction. These criteria encompass factors such as mechanical behavior, Martian structural loads, raw material accessibility, available sources, energy required for production, water requirement, curing and hardening time, possibility of using 3D printers, byproduct usefulness, conditions required for hardening and curing, importation requirements from Earth, production complexity, long-term durability and behavior under galactic cosmic rays (GCRs) and solar energetic particles (SEPs). The pros and cons of each cement/concrete option are thoroughly assessed, considering the harsh conditions on Mars. Additionally, the study highlights extra considerations that are crucial for onsite construction on Mars. To determine the best practical option for onsite construction and sustainable colonization, the proposed cements/concretes were compared using multi-scale spider/radar diagrams and a quantitative point of view. This perspective was enabled by assigning weights to each criterion through expert consultation, experimental data, and literature review, ensuring that the diagrams accurately reflect the features of each concrete mix. This comprehensive investigation aims to provide valuable insights into selecting the most suitable cement/concrete for onsite construction on Mars, considering the structural engineering perspective and the long-term goal of sustainable colonization.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 494-520"},"PeriodicalIF":3.1,"publicationDate":"2024-10-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142587324","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Exploring potential candidates of alternative solid hydrocarbon propellants for cold-gas thrusters","authors":"Thimthana Lee,&nbsp;Mahdi Davoodianidalik,&nbsp;Dimitrios Tsifakis,&nbsp;Roderick W. Boswell,&nbsp;Christine Charles","doi":"10.1016/j.actaastro.2024.10.047","DOIUrl":"10.1016/j.actaastro.2024.10.047","url":null,"abstract":"<div><div>Cold-gas thrusters play a vital role as a subsystem in satellite operations facilitating space maneuvers in numerous missions. Achieving optimal propulsion necessitates not only continuous development of thruster design but also an exploration of novel propellant options to enhance overall performance. While an ideal propellant remains elusive, many studies have identified alternative options to replace commonly used inert gases. Choosing a solid-state propellant offers benefits such as the absence of a pressurised tank and sloshing effect. Hydrocarbon propellants are advantageous due to their non-corrosiveness and abundance as organic compounds on Earth. The sublimation process for manipulating solid propellants typically requires only a few watts, making it suitable for low-power budget missions. This work presents five solid hydrocarbon propellants for cold-gas thrusters, three of which have not yet been experimentally explored. The comparison between various aspects, including mass flow rate, power consumption, and several key performance parameters, is discussed. The measured mass flow rate is a function of the species and temperature, following the trend of the vapour pressure. The power consumption for all propellants only depends on the required heating temperature as they share similar thermal properties. The thrust generated by each propellant is comparable and linearly proportional to the mass flow rate when the flow is choked. Specific impulse remains relatively constant across different mass flow rates due to the strong correlation between thrust and mass flow rate. The thrust-to-power ratio is generally comparable among the propellants, except hexamine, which demands more power at higher operating temperatures due to increased heat loss. Among these alternatives, camphor emerges as the most promising candidate due to its low power consumption, thrust generation, and mass efficiency. On the other hand, naphthalene offers the best in terms of its superior thrust-to-power ratio and cost-per-kilogram advantage.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 427-438"},"PeriodicalIF":3.1,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142572361","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}