Gotowe bibliografie tematyczne / Thrust specific impulse

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  1. Artykuły w czasopismach
  2. Rozprawy doktorskie
  3. Książki
  4. Części książek
  5. Streszczenia konferencji
  6. Raporty organizacyjne

Gotowa bibliografia na temat „Thrust specific impulse”

Autor: Grafiati
Data publikacji: 2 czerwca 2025
Data aktualizacji: 31 lipca 2025

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Artykuły w czasopismach na temat "Thrust specific impulse"

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Navalino, RDA, NRS Muda, MAE Hafizah, and Y. Ruyat. "Analysis of carbon nano particle variant as the propellant fuel to increase specific impulses of rockets." F1000Research 12 (May 29, 2024): 1414. http://dx.doi.org/10.12688/f1000research.138276.3.

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Background This study compares propellant fuels’ specific thrust and impulse parameters using nanocarbon variant fuels from coconut shells and coal. Specific impulses and impulses are essential parameters that determine rocket performance. The specific thrust and impulses are influenced by fuel type, material composition, heat flow, and burning time parameters. The characteristics of nanocarbon as a fuel are proven to have high-value features and a long combustion time. This parameter is essential to add value to specific thrusts and impulses. Methods The method to prove the quality of solid f
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Navalino, RDA, NRS Muda, MAE Hafizah, and Y. Ruyat. "Analysis of carbon nano particle variant as the propellant fuel to increase specific impulses of rockets." F1000Research 12 (October 26, 2023): 1414. http://dx.doi.org/10.12688/f1000research.138276.1.

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Background: This study compares propellant fuels' specific thrust and impulse parameters using nanocarbon variant fuels from coconut shells and coal. Specific impulses and impulses are essential parameters that determine rocket performance. The specific thrust and impulses are influenced by fuel type, material composition, heat flow, and burning time parameters. The characteristics of nanocarbon as a fuel are proven to have high-value features and a long combustion time. This parameter is essential to add value to specific thrusts and impulses. Methods: The method to prove the quality of solid
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Navalino, RDA, NRS Muda, MAE Hafizah, and Y. Ruyat. "Analysis of carbon nano particle variant as the propellant fuel to increase specific impulses of rockets." F1000Research 12 (December 11, 2023): 1414. http://dx.doi.org/10.12688/f1000research.138276.2.

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Background: This study compares propellant fuels’ specific thrust and impulse parameters using nanocarbon variant fuels from coconut shells and coal. Specific impulses and impulses are essential parameters that determine rocket performance. The specific thrust and impulses are influenced by fuel type, material composition, heat flow, and burning time parameters. The characteristics of nanocarbon as a fuel are proven to have high-value features and a long combustion time. This parameter is essential to add value to specific thrusts and impulses. Methods: The method to prove the quality of solid
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K., F. Oyedeko*1 &. A. Onyieagho2. "EFFECT OF PROPELLANT FORMULATION ON PROPELLANT PROPERTIES." INTERNATIONAL JOURNAL OF ENGINEERING SCIENCES & RESEARCH TECHNOLOGY 7, no. 8 (2018): 305–13. https://doi.org/10.5281/zenodo.1345623.

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This paper present the effect of propellant formulations on propellant properties is very crucial to the quality of propellant used in rocket motor. As poor propellant formulation usually leads to unstable combustion and this can lead to a total destruction of the entire structure of the solid rocket motor. For this research work, the centre compositions selected were based on calculation for percentage mass composition from the stoichiometric equation for the combustion process. Hollow bates grains used for the design consist of a mass of propellant of 6 kg, core diameter of 0.050m, throat di
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Berliand, M., and R. Ishchenko. "CALCULATION OF THE EXPANSION PROCESS OF THE FLOW OF WORKING BODY IN THE NOZZLE OF A LIQUID-PHASE NUCLEAR ROCKET ENGINE." Slovak international scientific journal, no. 95 (May 15, 2025): 86–92. https://doi.org/10.5281/zenodo.15427667.

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In this work, flow parameters of the working body (hydrogen) were calculated at the inlet, throat, and exit sections of the liquid-phase nuclear rocket engine nozzle. A method was proposed for determining the specific impulse of thrust while accounting for losses due to scattering, friction, and variations in the specific enthalpy of the working body caused by non-adiabatic effects. The calculated specific impulse exceeded 9500 m/s, significantly surpassing the performance of chemical rocket engines. The evaluation of the thermogasdynamic parameters of the working body expansion confirmed the
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Cook, Ronald, James A. Nabity, and John W. Daily. "Characterizing Propellants for Variable-Thrust/Specific Impulse Colloid Thrusters." Journal of Propulsion and Power 33, no. 6 (2017): 1325–31. http://dx.doi.org/10.2514/1.b36495.

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Kammash, Terry, Myoung-Jae Lee, and David I. Poston. "High-Thrust-High-Specific Impulse Gasdynamic Fusion Propulsion System." Journal of Propulsion and Power 13, no. 3 (1997): 421–27. http://dx.doi.org/10.2514/2.5180.

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Taheri, Ehsan, and John L. Junkins. "How Many Impulses Redux." Journal of the Astronautical Sciences 67, no. 2 (2019): 257–334. http://dx.doi.org/10.1007/s40295-019-00203-1.

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AbstractA central problem in orbit transfer optimization is to determine the number, time, direction, and magnitude of velocity impulses that minimize the total impulse. This problem was posed in 1967 by T. N. Edelbaum, and while notable advances have been made, a rigorous means to answer Edelbaum’s question for multiple-revolution maneuvers has remained elusive for over five decades. We revisit Edelbaum’s question by taking a bottom-up approach to generate a minimum-fuel switching surface. Sweeping through time profiles of the minimum-fuel switching function for increasing admissible thrust m
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Cojocea, Andrei Vlad, Ionuț Porumbel, Mihnea Gall, and Tudor Cuciuc. "Experimental Thrust and Specific Impulse Analysis of Pulsed Detonation Combustor." Applied Sciences 14, no. 14 (2024): 5999. http://dx.doi.org/10.3390/app14145999.

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Detonation combustion represents a significant advancement in efficiency over traditional deflagration methods. This paper presents a Pulsed Detonation Combustor (PDC) model that is designed with an aerodynamic mixing chamber featuring Hartmann–Sprenger resonators and crossflow injection. This design enhances operational cycle frequency and enables sustained detonation over short distances (below 200 mm). The PDC’s performance was evaluated through a comprehensive full-factorial experimental campaign, incorporating four factors with four discrete levels each. Testing was conducted using both h
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DHAMA, Sanjeev Kumar, T. K. JINDAL, and S. K. MANGAL. "Influence of Nozzle Type, Divergence Angle and Area Ratio on Impulse of Pulse Detonation Engine." INCAS BULLETIN 12, no. 2 (2020): 35–45. http://dx.doi.org/10.13111/2066-8201.2020.12.2.4.

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The influence of nozzle geometry on the impulse produced by the single cycle Pulse detonation engine (PDE) was experimentally investigated. For each experiment the nozzles were attached at the end of the engine. The impulse produced by the pulse detonation engine was calculated from the measured thrust. The thrust measurement was done by sliding the engine on the central bar of the thrust stand. The main structure of the basic PDE has a detonation tube with one terminal closed, a Schelkin spiral used as deflagration to detonation device, and a thrust stand to support the structure. Stoichiomet
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Rozprawy doktorskie na temat "Thrust specific impulse"

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Sakai, Tadashi. "A Study of Variable Thrust, Variable Specific Impulse Trajectories for Solar System Exploration." Diss., Georgia Institute of Technology, 2004. http://hdl.handle.net/1853/4904.

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A study has been performed to determine the advantages and disadvantages of variable thrust and variable specific impulse (Isp) trajectories for solar system exploration. There have been several numerical research efforts for variable thrust, variable Isp, power-limited trajectory optimization problems. All of these results conclude that variable thrust, variable Isp (variable specific impulse, or VSI) engines are superior to constant thrust, constant Isp (constant specific impulse, or CSI) engines. However, most of these research efforts assume a mission from Earth to Mars, and some of them
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Warner, Noah Zachary 1978. "Performance testing and internal probe measurements of a high specific impulse Hall thruster." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/38546.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003.<br>This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.<br>Page 116 blank.<br>Includes bibliographical references (p. 113-115).<br>The BHT-1000 high specific impulse Hall thruster was used for performance testing and internal plasma measurements to support the ongoing development of computational models. The thruster was performance tested in both single and two stage anode configurations. In the single
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Boyette, Wesley Ryan. "Thrust and specific impulse optimization of eight-centimeter valveless pulsejets at low subsonic flight speeds." 2008. http://www.lib.ncsu.edu/theses/available/etd-07252008-140723/unrestricted/etd.pdf.

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Książki na temat "Thrust specific impulse"

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Williams, Craig Hamilton. An analytic approximation to very high specific impulse and specific power interplanetary space mission analysis. National Aeronautics and Space Administration, 1995.

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M, Kazaroff John, Pavli Albert J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

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M, Kazaroff John, Pavli Albert J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

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M, Kazaroff John, Pavli Albert J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program, eds. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

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W, Haag Thomas, Manzella David H, and United States. National Aeronautics and Space Administration., eds. Operating characteristics of the Russian D-55 thruster with anode layer. National Aeronautics and Space Administration, 1994.

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United States. National Aeronautics and Space Administration., ed. The diagnostics of the external plasma for the plasma rocket: Final report, NASA Graduate Student Researchers Program, Johnson Space Center, contract number--NGT9-5. National Aeronautics and Space Administration, 1997.

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United States. National Aeronautics and Space Administration., ed. The diagnostics of the external plasma for the plasma rocket: Final report, NASA Graduate Student Researchers Program, Johnson Space Center, contract number--NGT9-5. National Aeronautics and Space Administration, 1997.

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N, Matossian J., and United States. National Aeronautics and Space Administration., eds. High-power ion thruster technology. National Aeronautics and Space Administration, 1996.

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N, Matossian J., and United States. National Aeronautics and Space Administration., eds. High-power ion thruster technology. National Aeronautics and Space Administration, 1996.

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N, Matossian J., and United States. National Aeronautics and Space Administration., eds. High power ion thruster technology. National Aeronautics and Space Administration, 1992.

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Części książek na temat "Thrust specific impulse"

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Huang, Minchao, Jianjun Wu, Jian Li, and Yuqiang Cheng. "Preface." In Solar Thermal Thruster. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-7490-6_1.

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AbstractThe continuous development of space exploration technology requires more efficient and economical space transport systems, and there is an urgent need for propulsion systems that are more efficient than chemical propulsion. Solar thermal propulsion (STP) systems have a relatively small size and high specific impulse, thus offering performance advantages in specific space missions. An STP system is generally composed of a concentrator, heat exchanger core, nozzle, and propellant supply system. The concentrator typically uses parabolic mirrors to concentrate sunlight to heat the heat exc
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Wu, Jianjun, Jian Li, Yuanzheng Zhao, and Yu Zhang. "Numerical Simulation of the PPT Discharge Process Based on Electromechanical Models." In Numerical Simulation of Pulsed Plasma Thruster. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-7958-1_5.

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AbstractZero-dimensional (0D) and one-dimensional (1D) models have low computational complexity and short computation time. In addition, these models can predict the macroscopic performance parameters of a pulsed plasma thruster (PPT), such as the specific impulse, impulse bit, and thrust efficiency. However, these models depend highly on experimental data and empirical parameters. Therefore, it is essential to establish a numerical model that can quickly and accurately predict the performance parameters of a PPT without relying on experimental results. In an electromechanical model, a PPT is
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Wu, Jianjun, Jian Li, Yuanzheng Zhao, and Yu Zhang. "Numerical Simulation of the Nanosecond Laser Ablation of Al Propellant." In Numerical Simulation of Pulsed Plasma Thruster. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-7958-1_4.

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AbstractPulsed plasma thrusters (PPTs) using gaseous propellants (Ziemer and Choueiri in Is the gas-fed PPT an electromagnetic accelerator an investigation using measured performance. AIAA 99–2289, 1999; Ziemer et al. in Performance characterization of a high efficiency gas-fed pulsed plasma thruster. AIAA-97–2925, 1997; Ziemer in Performance scaling of gas-fed pulsed plasma thrusters. Princeton University, 2001; Ziemer and Petr in Performance of gas fed pulsed plasma thrusters using water vapour propellant. AIAA 2002–4273, 2002) typically far outperform those using solid propellants in terms
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Ou, Yang, Yuqi Li, Yu Zhang, Jianjun Wu, and Yuqiang Cheng. "Impulse Measurement Methods for Space Micro-Propulsion Systems." In Propulsion Systems - Recent Advances, New Perspectives and Applications [Working Title]. IntechOpen, 2023. http://dx.doi.org/10.5772/intechopen.110865.

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Space micro-propulsion systems are increasingly considered an attractive option for station-keeping and drag-makeup purposes for the mass- and power-limited satellites due to their critical factors of simple design, small volume, and high specific impulse. These systems typically generate low-range thrust from nN to mN, and their impulses are less than mNs, making it difficult for conventional sensors to detect them directly. Consequently, the design of a special thrust stand is often necessary to measure these micro-propulsion systems. This chapter outlines recommended practices for the opera
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Singh, Sukhmander, Bhavna Vidhani, and Ashish Tyagi. "Numerical Investigations of Electromagnetic Oscillations and Turbulences in Hall Thrusters Using Two Fluid Approach." In Plasma Science and Technology [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.99883.

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The first part of the contributed chapter discuss the overview of electric propulsion technology and its requirement in different space missions. The technical terms specific impulse and thrust are explained with their relation to exhaust velocity. The shortcoming of the Hall thrusters and its erosion problems of the channel walls are also conveyed. The second part of the chapter discuss the various waves and electromagnetic instabilities propagating in a Hall thruster magnetized plasma. The dispersion relation for the azimuthal growing waves is derived analytically with the help of magnetohyd
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Zhang, Kai, Duo Zhang, Fei Qin, and Xuanfei Yu. "Numerical Investigation on Pendulum Geometric Throat Matching Characteristics of Dual-Mode Ramjet Combustor." In Advances in Transdisciplinary Engineering. IOS Press, 2025. https://doi.org/10.3233/atde250335.

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FABRE (Fan Augmented Air-Breathing Ramjet Engine) represents a hypersonic combined cycle power system with extensive applications in the aerospace industry, particularly in TSTO scenarios, capable of achieving speeds up to Mach 7. However, a persistent challenge lies in achieving optimal flow matching at high Mach numbers within the FABRE dual-mode scramjet combustor, characterized by a low length-to-diameter ratio. To address this challenge, this study employs numerical simulations to scrutinize the flow dynamics within the FABRE ramjet combustor across varying geometric throat areas at Mach
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"Application of Ion Thrusters to High-Thrust, High-Specifi c-Impulse Nuclear Electric Missions." In Nuclear Space Power and Propulsion Systems. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/5.9781600860096.0053.0126.

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Khan, Nasrullah, Abdul Rehman, Riffat Jabeen, Muzzammil Siraj, Ijaz Ahmed, and Atir Iftikhar. "The Intersection of AI in Finance and Healthcare." In Advances in Healthcare Information Systems and Administration. IGI Global, 2024. https://doi.org/10.4018/979-8-3693-6577-9.ch016.

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This exploration investigates the relinquishment trends, challenges, and profitable impacts of AI in the finance and healthcare sectors. The study reveals that while AI significantly enhances functional effectiveness and profitable returns in both fields, distinct sector-specific challenges must be addressed. In finance, rapid-fire integration of AI technologies leads to advancements in trading, threat operation, and client service, but compliance with nonsupervisory fabrics poses hurdles. In healthcare, AI-driven inventions ameliorate diagnostics and patient issues, yet ethical enterprises re
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Müller, Herta, Libuše Moníková, and Kerstin Hensel. "Herta Müller: ‘Das, was Von Innen Kam, Angesichts Des Äusseren’." In Body and Narrative in Contemporary Literatures in German. Oxford University PressOxford, 2005. http://dx.doi.org/10.1093/oso/9780199277766.003.0002.

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Abstract The structure underlying Herta Muller’s work is the notion of trauma, which unites the representation of the body with language and narrative strategies. In her work, the body remains the predominant and primary concern. Traumatic events evident in Muller’s texts are caused by, and rooted in, physical experience: torture and interrogation, threat of violence, and, ultimately, death. The body also acts as the impetus to writing for Muller, as her poetological essays make clear, describing this impulse in terms which recall the effects of trauma. Representations of the body dominate the
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Streszczenia konferencji na temat "Thrust specific impulse"

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Kovaleski, Scott, and Mark Kemp. "Thrust and Specific Impulse Measurements of the Ferroelectric Plasma Thruster." In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-5202.

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Lenguito, G., Juan Fernandez de la Mora, and A. Gomez. "Variable thrust/specific-impulse of multiplexed electrospray microthrusters." In 2013 IEEE Aerospace Conference. IEEE, 2013. http://dx.doi.org/10.1109/aero.2013.6497318.

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Pakhomov, Andrew V. "Ablative Laser Propulsion: A Study of Specific Impulse, Thrust and Efficiency." In BEAMED ENERGY PROPULSION: First International Symposium on Beamed Energy Propulsion. AIP, 2003. http://dx.doi.org/10.1063/1.1582108.

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Phipps, Claude R., James R. Luke, and Wesley Helgeson. "Laser-powered multi-newton thrust space engine with variable specific impulse." In High-Power Laser Ablation 2008, edited by Claude R. Phipps. SPIE, 2008. http://dx.doi.org/10.1117/12.786459.

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Li, J. F., Z. Che, and H. N. Li. "Applications of homotopic approach in variable-specific-impulse low-thrust trajectory optimization." In 2014 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC). IEEE, 2014. http://dx.doi.org/10.1109/cgncc.2014.7007501.

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WILBUR, PAUL, and JIAN-ZHANG HAN. "Constrained sheath optics for high thrust density, low specific impulse ion thrusters." In 19th International Electric Propulsion Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1073.

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Taheri, Ehsan. "Composite Smooth Control Method for Low-Thrust Trajectory Design: Variable Specific Impulse Engine." In AIAA Scitech 2020 Forum. American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-2184.

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Brainerd, Jerome, Aloysius I. Reisz, and Naveen Vetcha. "Generating Higher and Controllable Thrust and Specific Impulse with Electronic Cyclotron Resonance EP." In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-3957.

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Phipps, Claude R., James R. Luke, Wesley Helgeson, and Andrew V. Pakhomov. "Liquid-fueled, Laser-powered, N-class thrust Space Engine with Variable Specific Impulse." In BEAMED ENERGY PROPULSION: Fifth International Symposium on Beamed Energy Propulsion. AIP, 2008. http://dx.doi.org/10.1063/1.2931893.

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Lee, Riki, Brian D'Souza, Taylor Lilly, and Andrew Ketsdever. "Thrust Stand micro-Mass Balance Diagnostic Techniques for the Direct Measurement of Specific Impulse." In 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-5300.

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Raporty organizacyjne na temat "Thrust specific impulse"

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Shkurupiy, Valeria, and Nikita Budnyi. A priori estimation of instrumental error of energy characteristics of an electric rocket engine. Baltic State Technical University “VOENMEH” named after D.F.Ustinov, 2023. http://dx.doi.org/10.12731/edn:dkwobv.

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In this work, the power of the calculated electric rocket engine (ERE) requires thrust, specific impulse, and efficiency. ERE thrust measurement is interesting enough to achieve smallness of rapid growth. Specific impulse and efficiency are measured using laboratory methods. For this reason, one should naturally approach the choice of design parameters and the composition of the measuring system. One of the synthesis products can be the minimization of measurement errors. The paper approaches an approach to a priori instrumental estimation of the error determination, which may be useful in the
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