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Автор: Grafiati
Опубліковано: 14 березня 2023

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Статті в журналах з теми "Spacecraft Conceptual Design"

1

Weber, A., S. Fasoulas, and K. Wolf. "Conceptual interplanetary space mission design using multi-objective evolutionary optimization and design grammars." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 225, no. 11 (September 9, 2011): 1253–61. http://dx.doi.org/10.1177/0954410011407421.

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Анотація:
Conceptual design optimization (CDO) is a technique proposed for the structured evaluation of different design concepts. Design grammars provide a flexible modular modelling architecture. The model is generated by a compiler based on predefined components and rules. The rules describe the composition of the model; thus, different models can be optimized by the CDO in one run. This allows considering a mission design including the mission analysis and the system design. The combination of a CDO approach with a model based on design grammars is shown for the concept study of a near-Earth asteroid mission. The mission objective is to investigate two asteroids of different kinds. The CDO reveals that a mission concept using two identical spacecrafts flying to one target each is better than a mission concept with one spacecraft flying to two asteroids consecutively.
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2

Mosher, Todd. "Conceptual Spacecraft Design Using a Genetic Algorithm Trade Selection Process." Journal of Aircraft 36, no. 1 (January 1999): 200–208. http://dx.doi.org/10.2514/2.2426.

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3

Kurenkov, Vladimir, and Alexander Kucherov. "Experiences in engineering design training at Samara University." SHS Web of Conferences 137 (2022): 01013. http://dx.doi.org/10.1051/shsconf/202213701013.

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This paper aims to share experience gained by Samara National Research University in training students in engineering degree programme “Manned and Unmanned Spacecraft and Space Systems”. Core items of engineering degree curricula are projects because they basically form practical experience of future design engineers. Main items of the course project “Calculation of main parameters and generation of land remote sensing satellites conceptual design based on regard to required efficiency indices” are discussed. These include acquisition and processing of statistical data on space systems and satellites; determination of satellite orbit parameters; determination of massdimensional characteristics of spacecraft on-board systems and construction; formation of on-board systems; spacecraft construction models and assembly model; choice of launcher and spacehead model development. The activity is supported by appropriate training materials and software.
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4

Mahmoudi, M., A. B. Novinzadeh, and F. Pazooki. "Optimum conceptual design for the life support systems of manned spacecraft." Cogent Engineering 7, no. 1 (January 1, 2020): 1863304. http://dx.doi.org/10.1080/23311916.2020.1863304.

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5

Cuerno-Rejado, C., J. López-Díez, and A. Sanz-Andrés. "Rapid Method for Spacecraft Sizing." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 209, no. 3 (July 1995): 165–69. http://dx.doi.org/10.1243/pime_proc_1995_209_286_02.

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Анотація:
In this paper, a rapid method for spacecraft sizing is presented. This method is useful in both the conceptual and preliminary design phases of scientific and communication satellites. The aim of this method is to provide a sizing procedure similar to the ones used in the design of aircraft; actually by determining the mass of all the spacecraft subsystems. In the Introduction, the importance of an accurate initial mass budget in the design of satellites is emphasized. Literature about this topic is not very extensive and most of the existing methods have been recapitulated. The methodology followed in the proposed procedure for spacecraft mass sizing is based on these methods. Data from 26 existing satellites have been considered to obtain correlations between each subsystem mass and the mass of the whole spacecraft.
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6

Kerslake, Thomas W. "Effect of Voltage Level on Power System Design for Solar Electric Propulsion Missions." Journal of Solar Energy Engineering 126, no. 3 (July 19, 2004): 936–44. http://dx.doi.org/10.1115/1.1710523.

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This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission. A conceptual power system architecture was defined and design points were generated for several system voltages using state-of-the-art or advanced technologies. A 300-V “direct-drive” architecture was also analyzed to assess the benefits of directly powering the electric thruster from the photovoltaic array without up-conversion. Computational models were exercised to predict the performance and size power system components to meet spacecraft mission requirements. Pertinent space environments were calculated for the mission trajectory and an electron current collection model was developed to estimate photovoltaic array losses due to natural and induced plasma environments. The secondary benefits of power system mass savings for spacecraft propulsion and attitude control systems were also quantified. Results indicate that considerable spacecraft wet mass savings were achieved by the 300-V and 300-V direct-drive architectures.
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7

Polites, Michael E., John P. Sharkey, Gerald S. Nurre, Philip C. Calhoun, and William D. Lightsey. "Advanced X-ray Astrophysics Facility-Spectrometry Spacecraft Pointing Control System - Conceptual design." Journal of Spacecraft and Rockets 32, no. 2 (March 1995): 344–52. http://dx.doi.org/10.2514/3.26616.

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8

Markley, F. L., F. H. Bauer, J. J. Deily, and M. D. Femiano. "Attitude control system conceptual design for Geostationary Operational Environmental Satellite spacecraft series." Journal of Guidance, Control, and Dynamics 18, no. 2 (March 1995): 247–55. http://dx.doi.org/10.2514/3.21377.

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9

Nagasaki, Y., T. Nakamura, I. Funaki, Y. Ashida, and H. Yamakawa. "Conceptual Design of YBCO Coil With Large Magnetic Moment for Magnetic Sail Spacecraft." IEEE Transactions on Applied Superconductivity 23, no. 3 (June 2013): 4603405. http://dx.doi.org/10.1109/tasc.2013.2243791.

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10

De Souza, Ariana C. Caetano, and Walter A. Dos Santos. "11.1.2 SpaceESB - A Proposal of an Enterprise Service Bus for Spacecraft Conceptual Design." INCOSE International Symposium 21, no. 1 (June 2011): 1272–80. http://dx.doi.org/10.1002/j.2334-5837.2011.tb01284.x.

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Дисертації з теми "Spacecraft Conceptual Design"

1

Abreu, Michael N. "Conceptual design tools for the NPS spacecraft design center." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2001. http://handle.dtic.mil/100.2/ADA397230.

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2

Weber, A., S. Fasoulas, and K. Wolf. "Conceptual interplanetary space mission design using multi-objective evolutionary optimization and design grammars." Sage, 2011. https://publish.fid-move.qucosa.de/id/qucosa%3A38443.

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Анотація:
Conceptual design optimization (CDO) is a technique proposed for the structured evaluation of different design concepts. Design grammars provide a flexible modular modelling architecture. The model is generated by a compiler based on predefined components and rules. The rules describe the composition of the model; thus, different models can be optimized by the CDO in one run. This allows considering a mission design including the mission analysis and the system design. The combination of a CDO approach with a model based on design grammars is shown for the concept study of a near-Earth asteroid mission. The mission objective is to investigate two asteroids of different kinds. The CDO reveals that a mission concept using two identical spacecrafts flying to one target each is better than a mission concept with one spacecraft flying to two asteroids consecutively.
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3

Zimmer, Aline [Verfasser]. "Mission Analysis and Conceptual Spacecraft Design for Human Exploration of Near-Earth Asteroids / Aline Zimmer." München : Verlag Dr. Hut, 2012. http://d-nb.info/1029400342/34.

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Книги з теми "Spacecraft Conceptual Design"

1

L, Allen Cheryl, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Data base architecture for instrument characteristics critical to spacecraft conceptual design. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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2

Center, Lewis Research, ed. Conceptual design of a moving belt radiator shuttle-attached experiment: Technical requirements document. [Cleveland, Ohio]: National Aeronautics and Space Administration, [Lewis Research Center, 1989.

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3

Polites, Michael E. A conceptual design for the attitude control and determination system for the Magnetosphere Imager spacecraft. Huntsville, Ala: George C. Marshall Space Flight Center, 1995.

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4

H, Park Y., and Jet Propulsion Laboratory (U.S.), eds. Second-generation mobile satellite system: A conceptual design and trade-off study. Pasadena, Calif: National Aeronautics and Space Administration, Jet Propulsion Laboratory, California Institute of Technology, 1985.

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5

United States. National Aeronautics and Space Administration., ed. PC software graphics tool for conceptual design of space/planetary electrical power systems. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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6

United States. National Aeronautics and Space Administration., ed. PC software graphics tool for conceptual design of space/planetary electrical power systems. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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7

Center, Lewis Research, ed. Conceptual design of liquid droplet radiator shuttle-attached experiment: Final report. [Cleveland, Ohio]: Lewis Research Center, 1989.

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8

Center, Lewis Research, ed. Conceptual design of liquid droplet radiator shuttle-attached experiment: Final report. [Cleveland, Ohio]: Lewis Research Center, 1989.

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9

United States. National Aeronautics and Space Administration., ed. The determination of operational and support requirements and costs during the conceptual design of space systems: Interim report. Dayton, Ohio: University of Dayton, Engineering Management and Systems Dept., 1991.

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10

Pfeiffer, Shlomo L. Conceptual design of liquid droplet radiator shuttle-attached experiment: Technical requirements document. [Cleveland, Ohio]: Lewis Research Center, 1989.

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Частини книг з теми "Spacecraft Conceptual Design"

1

Maessen, D., J. Guo, E. Gill, B. Gunter, Q. P. Chu, G. Bakker, E. Laan, S. Moon, M. Kruijff, and G. T. Zheng. "Conceptual Design of the FAST-D Formation Flying Spacecraft." In Small Satellite Missions for Earth Observation, 155–63. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-03501-2_14.

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2

Thomson, Daniel M., Aleksandr Cherniaev, and Igor Telichev. "Conceptual Design of an “Umbrella” Spacecraft for Orbital Debris Shielding." In Space Safety is No Accident, 41–47. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-15982-9_5.

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3

de Souza, Ariana C. Caetano, and Walter A. dos Santos. "Automating Services for Spacecraft Conceptual Design Via an Enterprise Service Bus." In Advanced Concurrent Engineering, 159–66. London: Springer London, 2011. http://dx.doi.org/10.1007/978-0-85729-799-0_18.

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4

Ijichi, Koichi, Tetsuo Yamaguchi, Masao Sato, Kotaro Kiritani, and Kenichiro Sato. "The Conceptual System Design of the Users Spacecraft." In COSPAR Colloquia Series, 138–42. Elsevier, 1999. http://dx.doi.org/10.1016/s0964-2749(99)80018-3.

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5

Chell, Brian, Matthew J. Levine, Leigha Capra, Jerry J. Sellers, and Paul T. Grogan. "Conceptual Design of Space Missions Integrated with Real-Time, In Situ Sensors." In Advances in Transdisciplinary Engineering. IOS Press, 2022. http://dx.doi.org/10.3233/atde220664.

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Technological advances have enabled new types of distributed space missions (DSMs) that can improve the data resolution along many dimensions over monolithic, “flagship” spacecraft. Future DSMs will fuse data from a wide variety of sensors including other spacecraft and various ground- and air-based in situ platforms. The New Observing Strategies Testbed (NOS-T) is a new digital engineering environment based on systems engineering principles for simulating DSMs using a loosely coupled, event-driven architecture that manages communication between logically and geographically distributed user-developed applications. This paper demonstrates how NOS-T can evaluate new operational modes for satellite constellations using real-time stream gauge data from the U.S. Geological Survey (USGS) National Water Information System (NWIS) to decrease the latency of targeted spacecraft observations of flooded areas. The test case uses real-time data from NWIS stream gauges in the U.S., artificially triggers a flooding event, subsequently tasks satellite observations, and downlinks data to a ground station. It demonstrates how NOS-T enables the transfer of information between in situ and space-based sensors in a digital engineering environment to aid conceptual design of future DSMs across organizational boundaries.
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Тези доповідей конференцій з теми "Spacecraft Conceptual Design"

1

Zheng, Fei, and Mei Chen. "New Conceptual Design of Near-term Realizable Space Solar Power Satellite." In Spacecraft Structures Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-1512.

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2

Bromley, Blair P., John DeMora, Brett Casey, Paul Humm, Erik Kirstein, Amer Siddique, Jalal Javedani, George H. Miley, and Susan DelMedico. "Plasma focus spacecraft conceptual design study." In Proceedings of the 12th symposium on space nuclear power and propulsion: Conference on alternative power from space; Conference on accelerator-driven transmutation technologies and applications. AIP, 1995. http://dx.doi.org/10.1063/1.47151.

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3

Conde, Richard F., Kenneth A. Potocki, Adam Szabo, Karen W. Kirby, Haydee M. Maldonado, Paul B. Adamsen, Robert S. Bokulic, et al. "Optimization of Inner Heliospheric Sentinels Spacecraft Conceptual Design." In 2007 IEEE Aerospace Conference. IEEE, 2007. http://dx.doi.org/10.1109/aero.2007.352664.

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4

Brophy, John, and Steven Oleson. "Spacecraft Conceptual Design for Returning Entire Near-Earth Asteroids." In 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4067.

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5

Uebelhart, Scott, and David Miller. "Uncertainty Evaluation for Parameterized Spacecraft Architectures in Conceptual Design." In 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-2373.

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6

Mosher, Todd. "Applicability of selected Multidisciplinary Design Optimization methods to conceptual spacecraft design." In 6th Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-4052.

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7

Zhao, Hanmo, Zhaowei Sun, Dongyu Xu, and Dong Ye. "Overall Conceptual Design for Spacecraft System Based on Knowledge Engineering." In 2019 Chinese Control And Decision Conference (CCDC). IEEE, 2019. http://dx.doi.org/10.1109/ccdc.2019.8833297.

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8

de Weck, Olivier, Philip Springmann, and Darren Chang. "A Parametric Communications Spacecraft Model for Conceptual Design Trade Studies." In 21st International Communications Satellite Systems Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-2310.

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9

Fabisinski, Leo, and Charlotte Maples. "Risk Evaluation in the Pre-Phase A Conceptual Design of Spacecraft." In AIAA SPACE 2010 Conference & Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-8740.

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10

MARKLEY, F., F. BAUER, J. DEILY, and M. FEMIANO. "Attitude control system conceptual design for the GOES-N spacecraft series." In Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-2832.

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