Relevant bibliographies by topics / Spacecraft - Trajectory Optimization

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Spacecraft - Trajectory Optimization'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Spacecraft - Trajectory Optimization"

1

He, Hanqing, Peng Shi, and Yushan Zhao. "Hierarchical Optimization Algorithm and Applications of Spacecraft Trajectory Optimization." Aerospace 9, no. 2 (2022): 81. http://dx.doi.org/10.3390/aerospace9020081.

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The pursuit of excellent performance in meta-heuristic algorithms has led to a myriad of extensive and profound research and achievements. Notably, many space mission planning problems are solved with the help of meta-heuristic algorithms, and relevant studies continue to appear. This paper introduces a hierarchical optimization frame in which two types of particles—B-particles and S-particles—synergistically search for the optima. Global exploration relies on B-particles, whose motional direction and step length are designed independently. S-particles are for fine local exploitation near the
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Nan, Ying, GuoQiang Huang, YuPing Lu, and Ping Gong. "Global 4-D trajectory optimization for spacecraft." Science China Technological Sciences 53, no. 8 (2010): 2097–101. http://dx.doi.org/10.1007/s11431-010-3031-7.

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Hu, Yabo, Baolin Wu, Yunhai Geng, and Yunhua Wu. "Smooth time-optimal attitude control of spacecraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 7 (2018): 2331–43. http://dx.doi.org/10.1177/0954410018776531.

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In this paper, a trajectory optimization method for generating smooth and approximate time-optimal attitude maneuver trajectories of flexible spacecraft is proposed. Smooth attitude maneuver is highly desirable for flexible spacecraft, since vibration of flexible appendices can be suppressed. In order to obtain smooth and approximate time-optimal attitude trajectory, a novel objective function composed of two terms is developed in the problem of trajectory optimization: the first term is proportional to the total maneuver time and the other one is proportional to the integral of the squared co
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Dearing, Thomas L., John Hauser, Xudong Chen, Marco M. Nicotra, and Christopher Petersen. "Efficient Trajectory Optimization for Constrained Spacecraft Attitude Maneuvers." Journal of Guidance, Control, and Dynamics 45, no. 4 (2022): 638–50. http://dx.doi.org/10.2514/1.g006166.

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Liu, Hongzhao, and Benson H. Tongue. "Indirect Spacecraft Trajectory Optimization Using Modified Equinoctial Elements." Journal of Guidance, Control, and Dynamics 33, no. 2 (2010): 619–23. http://dx.doi.org/10.2514/1.45498.

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Mote, Mark, Magnus Egerstedt, Eric Feron, Andrew Bylard, and Marco Pavone. "Collision-Inclusive Trajectory Optimization for Free-Flying Spacecraft." Journal of Guidance, Control, and Dynamics 43, no. 7 (2020): 1247–58. http://dx.doi.org/10.2514/1.g004788.

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Rahimi, Afshin, Krishna Dev Kumar, and Hekmat Alighanbari. "Particle Swarm Optimization Applied to Spacecraft Reentry Trajectory." Journal of Guidance, Control, and Dynamics 36, no. 1 (2013): 307–10. http://dx.doi.org/10.2514/1.56387.

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Mengali, Giovanni, and Alessandro A. Quarta. "Trajectory Analysis and Optimization of Hesperides Mission." Universe 8, no. 7 (2022): 364. http://dx.doi.org/10.3390/universe8070364.

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A challenging problem from a technological viewpoint is to send a spacecraft at a distance of about 600 au from the Sun, comparable with that of the Sun’s gravitational focus (that is, the general relativistic focusing of light rays, whose minimum solar distance is obtained when the light rays are assumed to graze the Sun’s surface), and reach it in a time interval on the order of a human working lifetime. A suitably oriented telescope at that distance would be theoretically able to observe exoplanets tens of light years far away and possibly to discover new life forms. The transfer trajectory
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Shi, Jianlin, Jinbo Wang, Linfeng Su, Zhenwei Ma, and Hongbo Chen. "A Neural Network Warm-Started Indirect Trajectory Optimization Method." Aerospace 9, no. 8 (2022): 435. http://dx.doi.org/10.3390/aerospace9080435.

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The mission of spacecraft usually faces the problem of an unknown deep space environment, limited long-distance communication and complex environmental dynamics, which brings new challenges to the intelligence level and real-time performance of spacecraft onboard trajectory optimization algorithms. In this paper, the optimal control theory is combined with the neural network. Then, the state–control sample pairs and the state–costate sample pairs obtained from the high-fidelity algorithm are used to train the neural network and further drive the spacecraft to achieve optimal control. The propo
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Huang, Yan Yi, and Guo Dong Chen. "Indirect Optimization for Finite-Thrust Orbital Interception Problem." Applied Mechanics and Materials 313-314 (March 2013): 1051–54. http://dx.doi.org/10.4028/www.scientific.net/amm.313-314.1051.

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The nonlinear programming method is used to study the finite-thrust minimum-time orbital interception problem. Considering the spacecraft with fixed impulse, the Modified Equinoctial Elements are used to describe the movement of the spacecraft in the attached coordinate, and the model of the orbital interception problem is established. Then the trajectory optimization problem is solved by the nonlinear programming method. The simulations demonstrate that the minimum time orbital interception mission is well accomplished, and the spacecraft fly around the earth with maximum thrust magnitude at
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Dissertations / Theses on the topic "Spacecraft - Trajectory Optimization"

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Fitzgerald, Timothy J. "Spacecraft Trajectory Optimization Suite (STOpS): Optimization of Multiple Gravity Assist Spacecraft Trajectories Using Modern Optimization Techniques." DigitalCommons@CalPoly, 2015. https://digitalcommons.calpoly.edu/theses/1503.

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In trajectory optimization, a common objective is to minimize propellant mass via multiple gravity assist maneuvers (MGAs). Some computer programs have been developed to analyze MGA trajectories. One of these programs, Parallel Global Multiobjective Optimization (PaGMO), uses an interesting technique known as the Island Model Paradigm. This work provides the community with a MATLAB optimizer, STOpS, that utilizes this same Island Model Paradigm with five different optimization algorithms. STOpS allows optimization of a weighted combination of many parameters. This work contains a study on opti
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Sheehan, Shane P. "Spacecraft Trajectory Optimization Suite (STOPS): Optimization of Low-Thrust Interplanetary Spacecraft Trajectories Using Modern Optimization Techniques." DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1901.

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The work presented here is a continuation of Spacecraft Trajectory Optimization Suite (STOpS), a master’s thesis written by Timothy Fitzgerald at California Polytechnic State University, San Luis Obispo. Low-thrust spacecraft engines are becoming much more common due to their high efficiency, especially for interplanetary trajectories. The version of STOpS presented here optimizes low-thrust trajectories using the Island Model Paradigm with three stochastic evolutionary algorithms: the genetic algorithm, differential evolution, and particle swarm optimization. While the algorithms used here we
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Wase, Viktor. "High-Thrust Interplanetary Spacecraft Trajectory Optimization Using Cuda." Thesis, Uppsala universitet, Institutionen för informationsteknologi, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-372174.

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Global optimization applied to the design of high-thrust interplanetary space trajectories is a computationally expensive task. This thesis investigates the feasibility of combining the Multiple Gravity Assist model of spacecraft trajectory with periodic Lyapunov orbits. The trajectories are designed by optimization, enabled by the computational power of a high-end graphics processing unit.
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Graef, Jared. "B-Plane Targeting with the Spacecraft Trajectory Optimization Suite." DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2251.

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In interplanetary trajectory applications, it is common to design arrival trajectories based on B-plane target values. This targeting scheme, B-plane targeting, allows for specific target orbits to be obtained during mission design. A primary objective of this work was to implement B-plane targeting into the Spacecraft Trajectory Optimization Suite (STOpS). This work was based on the previous versions of STOpS done by Fitzgerald and Sheehan, however STOpS was redeveloped from MATLAB to python. This updated version of STOpS implements 3-dimensional computation, departure and arrival orbital pha
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Markopoulos, Nikos. "Analytical investigations in aircraft and spacecraft trajectory optimization and optimal guidance." Diss., Georgia Institute of Technology, 1994. http://hdl.handle.net/1853/12473.

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García, Ian Miguel. "Nonlinear trajectory optimization with path constraints applied to spacecraft reconfiguration maneuvers." Thesis, Massachusetts Institute of Technology, 2005. http://hdl.handle.net/1721.1/32448.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2005.<br>Includes bibliographical references (p. 115-120).<br>Future space assembly and science missions (e.g., Terrestrial Planet Finder) will typically require complex reconfiguration maneuvers involving well coordinated 6 DOF motions of the entire fleet of spacecraft. The motions must also satisfy constraints such as collision avoidance and pointing restrictions on some of the instruments. This problem is particularly difficult due to the nonlinearity of the attitude dynamics and the non-convexity o
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Malloy, Michael G. "Spacecraft Trajectory Optimization Suite (STOpS): Design and Optimization of Multiple Gravity-Assist Low-Thrust (MGALT) Trajectories Using Modern Optimization Techniques." DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2247.

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The information presented in the thesis is a continuation of the Spacecraft Trajectory Optimization Suite (STOpS). This suite was originally designed and developed by Timothy Fitzgerald and further developed by Shane Sheehan, both graduate students at California Polytechnic State University, San Luis Obispo. Spacecraft utilizing low-thrust transfers are becoming more and more common due to their efficiency on interplanetary trajectories, and as such, finding the most optimal trajectory between two planets is something of interest. The version of STOpS presented in this thesis uses Multiple Gra
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Arora, Nitin. "High performance algorithms to improve the runtime computation of spacecraft trajectories." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/49076.

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Challenging science requirements and complex space missions are driving the need for fast and robust space trajectory design and simulation tools. The main aim of this thesis is to develop new and improved high performance algorithms and solution techniques for commonly encountered problems in astrodynamics. Five major problems are considered and their state-of-the art algorithms are systematically improved. Theoretical and methodological improvements are combined with modern computational techniques, resulting in increased algorithm robustness and faster runtime performance. The five selected
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Shankar, G. S. "An Autonomous Guidance Scheme For Orbital Rendezvous." Thesis, Indian Institute of Science, 1995. https://etd.iisc.ac.in/handle/2005/129.

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The word 'rendezvous' implies a pre-arranged meeting between two entities for a specific purpose. This term is used in the study of spacecraft operations, to describe a set of maneuvers performed by two spacecraft in order to achieve a match in position and velocity. The term 'orbital rendezvous' applies to rendezvous between spacecraft in earth-centered orbits. Considering its obvious scope for application in the assembly, maintenance and retrieval of earth satellites, the importance of orbital rendezvous towards maintaining a sustained presence in space can be easily appreciated. This partic
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Shankar, G. S. "An Autonomous Guidance Scheme For Orbital Rendezvous." Thesis, Indian Institute of Science, 1995. http://hdl.handle.net/2005/129.

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The word 'rendezvous' implies a pre-arranged meeting between two entities for a specific purpose. This term is used in the study of spacecraft operations, to describe a set of maneuvers performed by two spacecraft in order to achieve a match in position and velocity. The term 'orbital rendezvous' applies to rendezvous between spacecraft in earth-centered orbits. Considering its obvious scope for application in the assembly, maintenance and retrieval of earth satellites, the importance of orbital rendezvous towards maintaining a sustained presence in space can be easily appreciated. This partic
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Books on the topic "Spacecraft - Trajectory Optimization"

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Conway, Bruce, ed. Spacecraft Trajectory Optimization. Cambridge University Press, 2009. http://dx.doi.org/10.1017/cbo9780511778025.

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Conway, Bruce A. Spacecraft trajectory optimization. Cambridge University Press, 2010.

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Markopoulos, Nikos. Analytical investigations in aircraft and spacecraft trajectory optimization and optimal guidance. Langley Research Center, 1995.

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Jet Propulsion Laboratory (U.S.), ed. Galileo: Earth avoidance study report. Jet Propulsion Laboratory, California Institute of Technology, 1988.

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United States. National Aeronautics and Space Administration., ed. Low thrust optimal orbital transfers, NAS8-38609 D.O. 64: Final report. National Aeronautics and Space Administration, 1994.

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Center, Langley Research, ed. An open loop guidance architecture for navigationally robust on-orbit docking. National Aeronautics and Space Administration, Langley Research Center, 1995.

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Markopoulos, Nikos. Analytical investigations in aircraft and spacecraft trajectory optimization and optimal guidance / by Nikos Markopoulos and Anthony J. Calise. National Aeronautics and Space Administration, Langley Research Center, 1995.

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R, Ellis Stephen, and Ames Research Center, eds. Interactive orbital proximity operations planning system instruction and training guide. National Aeronautics and Space Administration, Ames Research Center, 1994.

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D, Goodson Troy, Ledsinger Laura A, and United States. National Aeronautics and Space Administration., eds. Theory and computation of optimal low-and medium-thrust transfers. National Aeronautics and Space Administration, 1995.

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United States. National Aeronautics and Space Administration., ed. Theory and computation of optimal low- and medium-thrust transfers. National Aeronautics and Space Administration, 1994.

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Book chapters on the topic "Spacecraft - Trajectory Optimization"

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Miller, James. "Trajectory Optimization." In Planetary Spacecraft Navigation. Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-78916-3_4.

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Wei, Zhenyu, Lin Ma, Kexin Wang, and Zhijiang Shao. "Simultaneous Trajectory Optimization for Adaptive Powered Descent." In Autonomous Trajectory Planning and Guidance Control for Launch Vehicles. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-0613-0_6.

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AbstractThe powered descent phase is the terminal phase of the planetary descent and landing mission, where the required direction and magnitude of the thrust engine are determined to steer the spacecraft to meet the pre-determined targeting condition at the end, such as touchdown at the designated landing site with the required velocity [12].
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Simões, Luís F., Dario Izzo, Evert Haasdijk, and A. E. Eiben. "Multi-rendezvous Spacecraft Trajectory Optimization with Beam P-ACO." In Evolutionary Computation in Combinatorial Optimization. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-55453-2_10.

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Yang, Le-ping, Wei-wei Cai, and Yan-wei Zhu. "Flatness-Based Low-Thrust Trajectory Optimization for Spacecraft Proximity Operations." In Springer Optimization and Its Applications. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-41508-6_18.

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Zhang, Jinghui, Bin Yang, Guoqiang Zeng, Jinbo Wang, and Wei Teng. "Hybrid Successive Convex Programming for Spacecraft Electromagnetic Docking Trajectory Optimization." In Lecture Notes in Electrical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6613-2_345.

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Peng, Qian, Jianguo Guo, and Shengjiang Yang. "Genetic Algorithm-Based Re-Entry Trajectory Optimization and Footprint Determination for Lifting Body Spacecraft." In Lecture Notes in Electrical Engineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-8155-7_114.

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Li, Yongyuan, Yi Jiang, and Chunping Huang. "Trajectory Optimization and Analysis for Near Spacecraft’s Unpowered Gliding Phase." In Advances in Intelligent and Soft Computing. Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-28655-1_7.

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Olivio, Adilson Pedro. "Comparison of the Problem of Optimizing the Trajectory of a Spacecraft with a Perfectly Adjustable Engine for Two- And Three-Channel Control in the Vicinity of a Circular Orbit." In Principles of the New Ecosystem Formation: Multicultural Space. Publishing house Sreda, 2022. http://dx.doi.org/10.31483/r-102734.

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Within the framework of this work, a comparison of the problem of optimizing the trajectory of a spacecraft with an ideally controlled engine for two- and three-channel control in the vicinity of a circular orbit is proposed. New approaches are introduced to optimize the trajectories of spacecraft in closed form for two- and three-channel control. The Hill-Clohessy-Wiltshire equations are used to describe the motion of the spacecraft in the vicinity of a circular orbit. To solve the optimal control problem, the maximum principle is used. The results of the trajectory optimization problem for two- and three-channel control are compared. Numerical examples of optimal trajectories with an ideally regulated motor in the vicinity of a circular one are given.
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Conference papers on the topic "Spacecraft - Trajectory Optimization"

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Ulybyshev, Yuri. "Trajectory Optimization for Spacecraft Proximity Operations with Constraints." In AIAA Guidance, Navigation, and Control Conference. American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6629.

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WANG, TSENG-CHAN, RICHARD STANFORD, RICHARD SUNSERI, and PETER BRECKHEIMER. "Survey of optimization techniques for nonlinear spacecraft trajectory searches." In Astrodynamics Conference. American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4285.

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Ulybyshev, Yuri. "Spacecraft Trajectory Optimization Based on Discrete Sets of Pseudo-Impulses." In AIAA/AAS Astrodynamics Specialist Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-6276.

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Williams, Jacob, Robert D. Falck, and Izaak B. Beekman. "Application of Modern Fortran to Spacecraft Trajectory Design and Optimization." In 2018 Space Flight Mechanics Meeting. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1451.

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Zhou, Yang, and Linjie Kong. "Finite-thrust Spacecraft Trajectory optimization via Direct State Transition Method." In 2023 6th International Conference on Electronics Technology (ICET). IEEE, 2023. http://dx.doi.org/10.1109/icet58434.2023.10212074.

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Wang, Yong, Min Zhu, Yiheng Wei, and Yang Zhang. "Solar sail spacecraft trajectory optimization based on improved imperialist competitive algorithm." In 2012 10th World Congress on Intelligent Control and Automation (WCICA 2012). IEEE, 2012. http://dx.doi.org/10.1109/wcica.2012.6357865.

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OCAMPO, C. "AN ARCHITECTURE FOR A GENERALIZED SPACECRAFT TRAJECTORY DESIGN AND OPTIMIZATION SYSTEM." In Proceedings of the Conference. WORLD SCIENTIFIC, 2003. http://dx.doi.org/10.1142/9789812704849_0023.

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Runde, Zhang, Cai Weiwei, Yang Leping, and Fan Dawei. "Spacecraft relative trajectory planning under terminal angle constraints via convex optimization." In 2022 China Automation Congress (CAC). IEEE, 2022. http://dx.doi.org/10.1109/cac57257.2022.10055626.

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Malyuta, Danylo, Taylor Reynolds, Michael Szmuk, Behcet Acikmese, and Mehran Mesbahi. "Fast Trajectory Optimization via Successive Convexification for Spacecraft Rendezvous with Integer Constraints." In AIAA Scitech 2020 Forum. American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-0616.

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Kluever, C., and B. Pierson. "Vehicle and trajectory optimization of nuclear electric propulsion spacecraft for lunar missions." In 30th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-3255.

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