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Relevant bibliographies by topics / Continuous thrust propulsion

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Academic literature on the topic 'Continuous thrust propulsion'

Author: Grafiati

Published: 23 June 2021

Last updated: 4 February 2022

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Journal articles on the topic "Continuous thrust propulsion"

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Chen, J. H., J. Bull, and D. B. DeBra. "A Continuous Proportional Low-Thrust Propulsion System." IFAC Proceedings Volumes 22, no. 7 (1989): 223–29. http://dx.doi.org/10.1016/s1474-6670(17)53410-2.

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Akoz, Emre, and Keith W. Moored. "Unsteady propulsion by an intermittent swimming gait." Journal of Fluid Mechanics 834 (November 17, 2017): 149–72. http://dx.doi.org/10.1017/jfm.2017.731.

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Inviscid computational results are presented on a self-propelled swimmer modelled as a virtual body combined with a two-dimensional hydrofoil pitching intermittently about its leading edge. Lighthill (Proc. R. Soc. Lond. B, vol. 179, 1971, pp. 125–138) originally proposed that this burst-and-coast behaviour can save fish energy during swimming by taking advantage of the viscous Bone–Lighthill boundary layer thinning mechanism. Here, an additional inviscid Garrick mechanism is discovered that allows swimmers to control the ratio of their added-mass thrust-producing forces to their circulatory d

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Widhalm, J. W., and S. A. Heise. "Optimal in-plane orbital evasive maneuvers using continuous thrust propulsion." Journal of Guidance, Control, and Dynamics 14, no. 6 (1991): 1323–26. http://dx.doi.org/10.2514/3.20793.

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Mariaux, G., J. L. Peube, and Y. Gervais. "Inertia Effects on Pulsed Propulsion: Application to the Study of a Hydro-Propulsor." Journal of Ship Research 44, no. 02 (2000): 83–95. http://dx.doi.org/10.5957/jsr.2000.44.2.83.

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The marine propulsion systems that exist at the moment rely on the product creating an almost continuous flow in which the mechanical energy is given to the liquid in a continuous fashion. Here we study an original seawater propulsor in which the mechanical energy is provided to the liquid by the alternative displacement of a fluid contact surface. The produced flow is channeled towards the back of the vehicle that has to be propelled by a system of valves, in order to create an average positive thrust. These valves are free, so their operation is linked with the flow resulting from the intera

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Anderson, Pamela, and Malcolm Macdonald. "Extension of Highly Elliptical Earth Orbits Using Continuous Low-Thrust Propulsion." Journal of Guidance, Control, and Dynamics 36, no. 1 (2013): 282–92. http://dx.doi.org/10.2514/1.55304.

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Oliveira, Thais Carneiro, Evandro Marconi Rocco, José Leonardo Ferreira, and Antonio F. B. A. Prado. "Minimum Fuel Low-Thrust Transfers for Satellites Using a Permanent Magnet Hall Thruster." Mathematical Problems in Engineering 2013 (2013): 1–12. http://dx.doi.org/10.1155/2013/945030.

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Most of the satellite missions require orbital maneuvers to accomplish its goals. An orbital maneuver is an operation where the orbit of a satellite is changed, usually applying a type of propulsion. The maneuvers may have several purposes, such as the transfer of a satellite to its final orbit, the interception of another spacecraft, or the adjustment of the orbit to compensate the shifts caused by external forces. In this situation it is essential to minimize the fuel consumption to allow a greater number of maneuvers to be performed, and thus the lifetime of the satellite can be extended. T

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Solórzano, Carlos Renato Huaura, Antonio Fernando Bertachini de Almeida Prado, and Alexander Alexandrovich Sukhanov. "Outer Planet Missions with Electric Propulsion Systems—Part I." Mathematical Problems in Engineering 2010 (2010): 1–11. http://dx.doi.org/10.1155/2010/313571.

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For interplanetary missions, efficient electric propulsion systems can be used to increase the mass delivered to the destination. Outer planet exploration has experienced new interest with the launch of the Cassini and New Horizons Missions. At the present, new technologies are studied for better use of electric propulsion systems in missions to the outer planets. This paper presents low-thrust trajectories using the method of the transporting trajectory to Uranus, Neptune, and Pluto. They use nuclear and radio isotopic electric propulsion. These direct transfers have continuous electric propu

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Cao, Jing, Hengnian Li, and Hongxin Shen. "Orbital plane change maneuver strategy using electric propulsion." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 7 (2018): 2360–67. http://dx.doi.org/10.1177/0954410018779315.

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The orbital dynamics basis for orbital plane change maneuver using chemical propulsion is the impulsive orbital change theory in practical engineering. The orbital plane change theory using continuous thrust suitable for electric propulsion is studied in this paper. A set of nonsingular orbital variational equations using quaternion is used to investigate the orbital motion of spacecraft under constant normal acceleration departing from a Keplerian circular orbit firstly. Results show that the orbit of spacecraft under continuous constant normal acceleration is a circular orbit over the gravit

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Djojodihardjo, Harijono, and Ali Yousefian. "A Parametric Study of Interplanetary Mission Using Solar Sail." Applied Mechanics and Materials 629 (October 2014): 291–97. http://dx.doi.org/10.4028/www.scientific.net/amm.629.291.

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Solar sailing has been an attractive concept and possibly an alternative mean of space propulsion for decades to come since solar sail spacecrafts can generate thrust without requiring any propellant. While the resulting acceleration is small, the continuous thrust would lead to high speed. The present work serves to demonstrate the potential of solar sail by analyzing the dynamics of a spacecraft utilizing solar sail and by carrying out a parametric study for an interplanetary mission exemplified by specific trajectory to Mars.

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Zhou, Junfeng, Lin Zhao, Jianhua Cheng, Shuo Wang, and Yipeng Wang. "Pursuer’s Control Strategy for Orbital Pursuit-Evasion-Defense Game with Continuous Low Thrust Propulsion." Applied Sciences 9, no. 15 (2019): 3190. http://dx.doi.org/10.3390/app9153190.

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This paper studies the orbital pursuit-evasion-defense problem with the continuous low thrust propulsion. A control strategy for the pursuer is proposed based on the fuzzy comprehensive evaluation and the differential game. First, the system is described by the Lawden’s equations, and simplified by introducing the relative state variables and the zero effort miss (ZEM) variables. Then, the objective function of the pursuer is designed based on the fuzzy comprehensive evaluation, and the analytical necessary conditions for the optimal control strategy are presented. Finally, a hybrid method com

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Dissertations / Theses on the topic "Continuous thrust propulsion"

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Kim, Mischa. "Continuous Low-Thrust Trajectory Optimization: Techniques and Applications." Diss., Virginia Tech, 2005. http://hdl.handle.net/10919/27046.

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Trajectory optimization is a powerful technique to analyze mission feasibility during mission design. High-thrust trajectory optimization problems are typically formulated as discrete optimization problems and are numerically well-behaved. Low-thrust systems, on the other hand, operate for significant periods of the mission time. As a result, the solution approach requires continuous optimization; the associated optimal control problems are in general numerically ill-conditioned. In addition, case studies comparing the performance of low-thrust technologies for space travel have not received a

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Reinthal, Eric. "Relative Orbit Propagation and Control for Satellite Formation Flying using Continuous Low-thrust." Thesis, Luleå tekniska universitet, Institutionen för system- och rymdteknik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-61664.

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For the upcoming formation flying technology demonstration mission NetSat a relative orbit propagator as well as a relative orbit controller were developed. The formation will consist of four equal nano-satellites with an electric propulsion system for orbit correction manoeuvres. This demands the use of continuous low-thrust models for relative orbit control, which is a novel field. A software framework was developed which allows orbit simulations of the whole fleet in a fully non-linear environment. The final on-board relative propagator is based on the Gim-Alfriend STM and incorporates ecce

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Schoeffler, Lara Elaine. "Orbital Dynamics of Space Nuclear Propulsion Systems." Case Western Reserve University School of Graduate Studies / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=case1618332162764726.

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Books on the topic "Continuous thrust propulsion"

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Prussing, John E. Cooperative Rendezvous. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198811084.003.0008.

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Cooperative rendezvous involves two thrusting spacecraft. Optimal continuous thrust trajectories and impulsive thrust terminal maneuvers are analysed. Orbital rendezvous typically involves one thrusting (active) vehicle and one coasting (passive) target vehicle. However, a cooperative rendezvous can result in propellant savings if the masses and propulsive capabilities of the two vehicles are comparable.

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Book chapters on the topic "Continuous thrust propulsion"

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Chen, J. H., J. Bull, and D. B. DeBra. "A CONTINUOUS PROPORTIONAL LOW-THRUST PROPULSION SYSTEM." In Automatic Control in Aerospace 1989. Elsevier, 1990. http://dx.doi.org/10.1016/b978-0-08-037027-9.50035-5.

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Conference papers on the topic "Continuous thrust propulsion"

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Horisawa, Hideyuki, Sota Sumida, Ikkoh Funaki, Claude Phipps, Kimiya Komurasaki, and John Sinko. "Thrust Generation with Low-Power Continuous-Wave Laser and Aluminum Foil Interaction." In BEAMED ENERGY PROPULSION: 6th International Symposium. AIP, 2010. http://dx.doi.org/10.1063/1.3435433.

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Schmidt, Tanja, Bernd Dachwald, Wolfgang Seboldt, and Monika Auweter-Kurtz. "Flight Opportunities from Mars to Earth for Piloted Missions Using Continuous Thrust Propulsion." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4573.

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Gater, Brittany, Jeffrey Feaster, and Javid Bayandor. "Dynamics and Propulsive Efficiency of Bio-Inspired Undulatory Marine Locomotion." In ASME 2016 Fluids Engineering Division Summer Meeting collocated with the ASME 2016 Heat Transfer Summer Conference and the ASME 2016 14th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/fedsm2016-7742.

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Computational fluid dynamics (CFD) was used to investigate the fluid mechanics for undulatory stingray locomotion. This method of undulatory propulsion can be utilized to generate non-turbulent thrust with minimal disturbance to the immediate environment, ideal for exploratory vehicles for underwater environments. Undulatory locomotion was modeled as a two-dimensional fin in free flow with a deforming non-slip boundary to represent a propagating sinusoidal wave with a linearly increasing amplitude, constant frequency, wavelength and flow velocity. In the presented computational study, we varie

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Belibassakis, K. A., Th P. Gerostathis, and G. K. Politis. "Calculation of Ship Hydrodynamic Propulsion in Rough Seas by Non-Linear BEM With Application to Reduction of Energy Losses in Waves." In ASME 2013 32nd International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/omae2013-10599.

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Environmental conditions corresponding to realistic sea states (which can be rarely considered calm) significantly affect ship propulsion due to added wave resistance, wind resistance and other factors, as e.g., continuous rudder motion for steering in adverse conditions. In addition, external factors such as ocean currents, which determine the actual flow on the ship, critically affect the actual behavior of the propulsion system. All the above cause significant additional energy losses that sometimes could drive the propulsion system of a ship at its limits. On the other hand, the operation

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GORBUNKOV, V. I., V. V. SHALAY, and N. V. PUSTOVOI. "THE SUPERSONIC ARGON FLOW PARAMETERS IN AN ARCJET THRUSTER." In 12TH INTERNATIONAL COLLOQUIUM ON PULSED AND CONTINUOUS DETONATIONS. TORUS PRESS, 2020. http://dx.doi.org/10.30826/icpcd12a29.

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A small closed volume occupied by the gas plasma is a specific feature of the propulsion systems for orbit correction of spacecraft (PSSC). We found the temperature of argon in the PSSC chamber using emission spectroscopy methods in the approximation of partial local thermal equilibrium.

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Kuninaka, Hitoshi, Shin Satori, and Yasuo Horiuchi. "Continuous operation test of microwave discharge ion thruster system." In 31st Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3070.

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Tsutahara, Michihisa, Kazuhiko Ogawa, Masahiko Sakamoto, and Takahiro Matsui. "Nozzle Flow of a Ship Propulsion Equipment Driven by High-Pressure Gas." In ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/fedsm2003-45092.

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A two-dimensional open type nozzle has been investigated for ship propulsion equipment. In this nozzle, a high-pressure gas (air) is ejected from below into water flow and accelerates the water towards downstream. Two cases, continuously and intermittently ejection of gas, are studied. In the latter case, the thrust itself is smaller than that in the former case, but thrust based on the ejection duration is larger. Even in the continuously ejected case, it was found that the gas phase and the water phase are separated. The water waves of large amplitude appear on the interface inside the nozzl

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Onda, Masahiko. "Experimental Study on Continuous Liquid Propellant Supply Mechanisms for Water Cannon Laser Thruster." In BEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion. AIP, 2006. http://dx.doi.org/10.1063/1.2203272.

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SAKIYAMA, M., A. IWATA, M. YOSHIWA, R. YOSHIDA, and Y. KAGAYA. "Continuous operation test of quasi-steady MPD thruster with a ring coil." In 19th International Electric Propulsion Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1045.

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Tobias, J., D. Depperschmidt, C. Welch, et al. "OH* Chemiluminescence Imaging of the Combustion Products From a Methane-Fueled Rotating Detonation Engine." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-77255.

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Pressure gain combustion (PGC) has been conceived to convert fuel’s chemical energy into thermal energy and mechanical energy, thereby reducing the entropy production in the process. Recent research has shown that the rotating detonation combustion or combustor (RDC) can provide excellent specific thrust, specific impulse, and pressure gain within a small volume through rapid energy release by continuous detonation in the circumferential direction. The RDC as a PGC system for power generating gas turbines in combined cycle power plants could provide significant efficiency gains. However, few p

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