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Letteratura scientifica selezionata sul tema "Orbit method"

Autore: Grafiati

Pubblicato: 4 giugno 2021

Ultima modifica: 2 febbraio 2022

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Articoli di riviste sul tema "Orbit method"

1

Chen, Q., J. D. Meiss, and I. C. Percival. "Orbit extension method for finding unstable orbits." Physica D: Nonlinear Phenomena 29, no. 1-2 (November 1987): 143–54. http://dx.doi.org/10.1016/0167-2789(87)90051-0.

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2

Song, Xu Min, Yong Chen, and Qi Lin. "Orbit Plan Method for General Rendezvous Problems." Applied Mechanics and Materials 543-547 (March 2014): 1385–88. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.1385.

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The orbit plan method of rendezvous mission was studied in this paper. We are concerned with the general rendezvous problem between two satellites which may be in non-coplanar, eccentric orbits, considering orbit perturbation and rendezvous time limitation. The planning problem was modeled as a nonlinear optimization problem, and the adaptive simulated annealing method was used to get the global solution. The Lambert algorithm was used to compute the transfer orbit, so that the endpoint constraint of rendezvous was eliminated. A shooting technique was used to solve the perturbed lambert problem. The method was validated by simulation results.

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3

Wang, Qianxin, Chao Hu, and Ya Mao. "Correction Method for the Observed Global Navigation Satellite System Ultra-Rapid Orbit Based on Dilution of Precision Values." Sensors 18, no. 11 (November 12, 2018): 3900. http://dx.doi.org/10.3390/s18113900.

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For ultra-rapid orbits provided by the Global Navigation Satellite System (GNSS), the key parameters, accuracy and timeliness, must be taken into consideration in real-time and near real-time applications. However, insufficient observations in later epochs appear to generate low accuracy in observed orbits, for which a correlation between the Dilution of Precision (DOP) of the orbit parameters and their accuracy is found. To correct the observed GNSS ultra-rapid orbit, a correction method based on the DOP values is proposed by building the function models between DOP values and the orbit accuracy. With 10-day orbit determination experiments, the results show that the observed ultra-rapid-orbit errors, generated by insufficient observations, can be corrected by 12–22% for the last three hours of the observed orbits. Moreover, considering the timeliness constraints in ultra-rapid-orbit determination, a DOP amplification factor is defined to weight the contribution of each tracking station and optimize the station distribution in the orbit determination procedure. Finally, six schemes are designed to verify the method and strategy in determining the ultra-rapid orbit based on one-month observations. The orbit accuracy is found to decrease by 1.27–6.34 cm with increasing amplification factor from 5–20%. Thus, the observed ultra-orbit correction method proposed is ideal when considering accuracy and timeliness in ultra-rapid orbit determination.

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4

Zhang, Mingjie, Jiangang Yang, Wanfu Zhang, and Qianlei Gu. "Orbit Decomposition Method for Rotordynamic Coefficients Identification of Annular Seals." Applied Sciences 11, no. 9 (May 7, 2021): 4237. http://dx.doi.org/10.3390/app11094237.

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The elliptical orbit whirl model is widely used to identify the frequency-dependent rotordynamic coefficients of annular seals. The existing solution technique of an elliptical orbit whirl model is the transient computational fluid dynamics (CFD) method. Its computational time is very long. For rapid computation, this paper proposes the orbit decomposition method. The elliptical whirl orbit is decomposed into the forward and backward circular whirl orbits. Under small perturbation circumstances, the fluid-induced forces of the elliptical orbit model can be obtained by the linear superposition of the fluid-induced forces arising from the two decomposed circular orbit models. Due to that the fluid-induced forces of circular orbit, the model can be calculated with the steady CFD method, and the transient computations can be replaced with steady ones when calculating the elliptical orbit whirl model. The computational time is significantly reduced. To validate the present method, its rotordynamic results are compared with those of the transient CFD method and experimental data. Comparisons show that the present method can accurately calculate the rotordynamic coefficients. Elliptical orbit parameter analysis reveals that the present method is valid when the whirl amplitude is less than 20% of seal clearance. The effect of ellipticity on rotordynamic coefficients can be ignored.

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5

Feng, Jingjing, Qichang Zhang, Wei Wang, and Shuying Hao. "A New Approach of Asymmetric Homoclinic and Heteroclinic Orbits Construction in Several Typical Systems Based on the Undetermined Padé Approximation Method." Mathematical Problems in Engineering 2016 (2016): 1–10. http://dx.doi.org/10.1155/2016/8585290.

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In dynamic systems, some nonlinearities generate special connection problems of non-Z2symmetric homoclinic and heteroclinic orbits. Such orbits are important for analyzing problems of global bifurcation and chaos. In this paper, a general analytical method, based on the undetermined Padé approximation method, is proposed to construct non-Z2symmetric homoclinic and heteroclinic orbits which are affected by nonlinearity factors. Geometric and symmetrical characteristics of non-Z2heteroclinic orbits are analyzed in detail. An undetermined frequency coefficient and a corresponding new analytic expression are introduced to improve the accuracy of the orbit trajectory. The proposed method shows high precision results for the Nagumo system (one single orbit); general types of non-Z2symmetric nonlinear quintic systems (orbit with one cusp); and Z2symmetric system with high-order nonlinear terms (orbit with two cusps). Finally, numerical simulations are used to verify the techniques and demonstrate the enhanced efficiency and precision of the proposed method.

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6

Ye, Fei, Yunbin Yuan, Bingfeng Tan, Zhiguo Deng, and Jikun Ou. "The Preliminary Results for Five-System Ultra-Rapid Precise Orbit Determination of the One-Step Method Based on the Double-Difference Observation Model." Remote Sensing 11, no. 1 (December 29, 2018): 46. http://dx.doi.org/10.3390/rs11010046.

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The predicted parts of ultra-rapid orbits are important for (near) real-time Global Navigation Satellite System (GNSS) precise applications; and there is little research on GPS/GLONASS/BDS/Galileo/QZSS five-system ultra-rapid precise orbit determination; based on the one-step method and double-difference observation model. However; the successful development of a software platform for solving five-system ultra-rapid orbits is the basis of determining and analyzing these orbits. Besides this; the different observation models and processing strategies facilitate to validate the reliability of the various ultra-rapid orbits. In this contribution; this paper derives the double-difference observation model of five-system ultra-rapid precise orbit determination; based on a one-step method; and embeds this method and model into Bernese v5.2; thereby forming a new prototype software platform. For validation purposes; 31 days of real tracking data; collected from 130 globally-distributed International GNSS Service (IGS) multi-GNSS Experiment (MGEX) stations; are used to determine a five-system ultra-rapid precise orbit. The performance of the software platform is evaluated by analysis of the orbit discontinuities at day boundaries and by comparing the consistency with the MGEX orbits from the Deutsches GeoForschungsZentrum (GFZ); between the results of this new prototype software platform and the ultra-rapid orbit provided by the International GNSS Monitoring and Assessment System (iGMAS) analysis center (AC) at the Institute of Geodesy and Geophysics (IGG). The test results show that the average standard deviations of orbit discontinuities in the three-dimension direction are 0.022; 0.031; 0.139; 0.064; 0.028; and 0.465 m for GPS; GLONASS; BDS Inclined Geosynchronous Orbit (IGSO); BDS Mid-Earth Orbit (MEO); Galileo; and QZSS satellites; respectively. In addition; the preliminary results of the new prototype software platform show that the consistency of this platform has been significantly improved compared to the software package of the IGGAC.

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7

Qin, Huang, Zhang, Wang, Yan, Xie, Cao, and Wang. "Precise Orbit Determination for BeiDou GEO/IGSO Satellites during Orbit Maneuvering with Pseudo-Stochastic Pulses." Remote Sensing 11, no. 21 (November 4, 2019): 2587. http://dx.doi.org/10.3390/rs11212587.

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In order to provide better service for the Asia-Pacific region, the BeiDou navigation satellite system (BDS) is designed as a constellation containing medium earth orbit (MEO), geostationary earth orbit (GEO), and inclined geosynchronous orbit (IGSO). However, the multi-orbit configuration brings great challenges for orbit determination. When orbit maneuvering, the orbital elements of the maneuvered satellites from broadcast ephemeris are unusable for several hours, which makes it difficult to estimate the initial orbit in the process of precise orbit determination. In addition, the maneuvered force information is unknown, which brings systematic orbit integral errors. In order to avoid these errors, observation data are removed from the iterative adjustment. For the above reasons, the precise orbit products of maneuvered satellites are missing from IGS (international GNSS (Global Navigation Satellite System) service) and iGMAS (international GNSS monitoring and assessment system). This study proposes a method to determine the precise orbits of maneuvered satellites for BeiDou GEO and IGSO. The initial orbits of maneuvered satellites could be backward forecasted according to the precise orbit products. The systematic errors caused by unmodeled maneuvered force are absorbed by estimated pseudo-stochastic pulses. The proposed method for determining the precise orbits of maneuvered satellites is validated by analyzing data of stations from the Multi-GNSS Experiment (MGEX). The results show that the precise orbits of maneuvered satellites can be estimated correctly when orbit maneuvering, which could supplement the precise products from the analysis centers of IGS and iGMAS. It can significantly improve the integrality and continuity of the precise products and subsequently provide better precise products for users.

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8

OLDEMAN, BART E., ALAN R. CHAMPNEYS, and BERND KRAUSKOPF. "HOMOCLINIC BRANCH SWITCHING: A NUMERICAL IMPLEMENTATION OF LIN'S METHOD." International Journal of Bifurcation and Chaos 13, no. 10 (October 2003): 2977–99. http://dx.doi.org/10.1142/s0218127403008326.

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We present a numerical method for branch switching between homoclinic orbits to equilibria of ODEs computed via numerical continuation. Starting from a 1-homoclinic orbit our method allows us to find and follow an N-homoclinic orbit, for any N>1 (if it exists nearby). This scheme is based on Lin's method and it is robust and reliable. The method is implemented in AUTO/HOMCONT. A system of ordinary differential equations introduced by Sandstede featuring inclination and orbit flip bifurcations and homoclinic-doubling cascades, is used as a test bed for the algorithm. It is also successfully applied to reliably find multihump traveling wave solutions in the FitzHugh–Nagumo nerve-axon equations and in a fourth-order Hamiltonian system arising as a model for water waves.

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9

Kong, Qiaoli, Fan Gao, Jinyun Guo, Litao Han, Linggang Zhang, and Yi Shen. "Analysis of Precise Orbit Predictions for a Hy-2A Satellite with Three Atmospheric Density Models Based on Dynamic Method." Remote Sensing 11, no. 1 (December 27, 2018): 40. http://dx.doi.org/10.3390/rs11010040.

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HY-2A (Haiyang 2A) is the first altimetry satellite in China, and it was designed to be in a repeated ground track orbit to achieve the mission targets. Maneuvers are necessary to keep the satellite on the designed orbit according to the dynamic precise orbital prediction. Atmospheric density models are essential for predicting the low Earth orbit (LEO) satellites, such as HY-2A. Nevertheless, it is a complex process to determine the optimal atmospheric density model for orbit prediction. In this paper, short-term and long-term orbit predictions based on the dynamic method using three different atmospheric density models are tested. Detailed comparisons and evaluation of the accuracy of the predicted results are performed. Furthermore, to assess the results for the ground tracking of the satellite, the interpolation method especially for a spherical surface is introduced. The results show that among the three models, the Jacchia 1971 model is in the closest agreement with Multi-Mission Ground Segment for Altimetry precise positioning and Orbitography (SSALTO) precise orbits. The root-mean-squares (RMSs) of radial orbit differences between the predicted and precise orbits are 0.016 m, 0.091 m, 0.176 m, 0.573 m, and 1.421 m for predicted 1-h, 12-h, 1-day, 3-day, and 7-day arcs, respectively.

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10

Lu, Qiuying, and Vincent Naudot. "Bifurcation Complexity from Orbit-Flip Homoclinic Orbit of Weak Type." International Journal of Bifurcation and Chaos 26, no. 04 (April 2016): 1650059. http://dx.doi.org/10.1142/s0218127416500590.

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In this paper, we study the unfolding of a three-dimensional vector field having an orbit-flip homoclinic orbit of weak type. Such a homoclinic orbit is a degenerate version of the so-called orbit-flip homoclinic orbit. We show the existence of inclination-flip homoclinic orbits of arbitrary higher order bifurcating from the unperturbed system. Our strategy consists of using the local moving coordinates method and blow up in the parameter space. In addition, the numerical existence of the orbit-flip homoclinic orbit of weak type is presented based on the truncated Taylor expansion and the numerical computation for both the strong stable manifold and unstable manifold.

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Tesi sul tema "Orbit method"

1

Mohamed, Ben Hadj Rhouma. "On the continuation of periodic orbits /." free to MU campus, to others for purchase, 1999. http://wwwlib.umi.com/cr/mo/fullcit?p9953845.

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2

Litsgård, Malte. "The Orbit Method and Geometric Quantisation." Thesis, Uppsala universitet, Analys och sannolikhetsteori, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-351508.

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3

Stevens, Robert E. "Design of optimal cyclers using solar sails." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Dec%5FStevens.pdf.

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Thesis (Aeronautical and Astronautical Engineer)--Naval Postgraduate School, December 2002.<br>Thesis advisor(s): I. Michael Ross, Dennis Byrnes. Includes bibliographical references (p. 119-120). Also available online.

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4

Koblick, Darin C. "Parallel high-precision orbit propagation using the modified Picard-Chebyshev method." California State University, Long Beach, 2013.

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5

Elvidge, Michael Edward Carleton University Dissertation Engineering Mechanical and Aerospace. "A stochastic method for calculating spacecraft vulnerability to low earth orbit debris." Ottawa, 1994.

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6

Hart, Andrew Markland Stanley. "Application of the homotopy continuation method to low-eccentricity preliminary orbit determination." Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/42500.

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7

Sheng, Liu Dong. "A New Method for Refinning Orbit of CPS Satellite Using Phase Measurement." International Foundation for Telemetering, 1990. http://hdl.handle.net/10150/613778.

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International Telemetering Conference Proceedings / October 29-November 02, 1990 / Riviera Hotel and Convention Center, Las Vegas, Nevada<br>This paper developed a new method of refinning GPS satellite orbit using phase measurement without knowing the GPS codes. Because this approach have no connection with any particular physical model, avoiding introducing any dynamic error, this method make it possible to get high precision GPS satellite orbit. A simulation computation has been conducted and gave an encouraging result.

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8

Scott, Karen Patricia 1964. "Radiometric calibration of on-orbit satellite sensors using an improved cross-calibration method." Diss., The University of Arizona, 1998. http://hdl.handle.net/10150/282831.

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As the field of remote sensing continues to grow with the launches of many new and complex satellite sensors in the next year, the ability to provide absolute calibration of these sensors becomes paramount for the many environmental studies proposed. In particular, temporal studies that monitor global changes in atmospheric constituents, ocean and terrestrial temperatures, and vegetation require that changes in the sensor itself, over the period of the study, be understood so that the data may be corrected. Numerous studies have established that satellite sensors change in orbit with respect to preflight calibration, in some cases, up to 20% or more over periods of three years. This research describes the development of an improved cross-calibration method of on-orbit satellite sensor radiometric calibration. The objective of the cross-calibration method is to transfer one sensor's calibration to another sensor which is typically difficult or expensive to calibrate with other methods. The cross-calibration method is relatively inexpensive to apply, and therefore there was a strong incentive to improve the application of the method and the understanding of the uncertainties associated with the method. The primary effort in this work has been the development of a cross-calibration software program which provides the means to easily perform end-to-end cross-calibrations. The program allows for a multiplicity of sites to be run, provides a search mechanism in order to identify calibration sites with particular characteristics, and contains an extensive error analysis capability. As part of this work, a search for acceptable cross-calibration sites was also performed which would allow a reduction in uncertainties of the method. Calibrations of five different sensor band pairs using System Pour l'Observation de la Terre (SPOT) 3, Landsat Thematic Mapper, and Advanced Very High Resolution Radiometer (AVHRR) sensors are performed. Very good results are obtained when the results are compared with other more expensive calibration methods, and the calibrations yielded uncertainties lower than reported in previous work.

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9

Van, Beusekom Craig Joseph. "A new guidance method for a DeltaV and re-entry constrained orbit transfer problem." Thesis, Massachusetts Institute of Technology, 2005. http://hdl.handle.net/1721.1/46571.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2005.<br>Includes bibliographical references (p. 153-154).<br>This thesis proposes a spacecraft guidance system designed for a unique class of orbit transfer problems. It considers a vehicle that undertakes a maneuver with the objective of precisely flying through a point in space at a particular time. The spacecraft must automatically determine a transfer orbit that will take it from a circular, low-earth parking orbit to a velocity-unconstrained rendezvous with a Keplerian trajectory. A constraint exists that both the final transfer orbit and the ultimate paths of any additional stages must lead rapidly to atmospheric reentry, typically within one revolution. Constrained to a fixed [delta]V resulting from a two stage thrust profile, the spacecraft must execute a burn maneuver that can effectively dissipate energy to place it on a transfer orbit with previously unknown velocity requirements. Finally, the guidance strategy should be robust to the uncertainties typically encountered in real spacecraft orbit transfer problems. In order to meet these constraints, this thesis first develops new analytic analysis of the relationship between reentry, perigee, and [delta]V. Next, a framework is developed for selecting a favorable transfer orbit while considering the various hard and soft constraints in the problem. Following transfer orbit selection, a plane of maneuver is calculated that maximizes likelihood of first stage reentry. Then traditional guidance strategies are adapted to the problem and hypothetical spacecraft design to produce a closed loop guidance solution. Results are presented that demonstrate the effectiveness of the new method.<br>by Craig Joseph Van Beusekom.<br>S.M.

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Bengtsson, Bernander Karl. "A Method for Detecting Resident Space Objects and Orbit Determination Based on Star Trackers and Image Analysis." Thesis, Uppsala universitet, Avdelningen för visuell information och interaktion, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-236873.

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Satellites commonly use onboard digital cameras, called star trackers. A star tracker determines the satellite's attitude, i.e. its orientation in space, by comparing star positions with databases of star patterns. In this thesis, I investigate the possibility of extending the functionality of star trackers to also detect the presence of resident space objects (RSO) orbiting the earth. RSO consist of both active satellites and orbital debris, such as inactive satellites, spent rocket stages and particles of different sizes. I implement and compare nine detection algorithms based on image analysis. The input is two hundred synthetic images, consisting of a portion of the night sky with added random Gaussian and banding noise. RSO, visible as faint lines in random positions, are added to half of the images. The algorithms are evaluated with respect to sensitivity (the true positive rate) and specificity (the true negative rate). Also, a difficulty metric encompassing execution times and computational complexity is used. The Laplacian of Gaussian algorithm outperforms the rest, with a sensitivity of 0.99, a specificity of 1 and a low difficulty. It is further tested to determine how its performance changes when varying parameters such as line length and noise strength. For high sensitivity, there is a lower limit in how faint the line can appear. Finally, I show that it is possible to use the extracted information to roughly estimate the orbit of the RSO. This can be accomplished using the Gaussian angles-only method. Three angular measurements of the RSO positions are needed, in addition to the times and the positions of the observer satellite. A computer architecture capable of image processing is needed for an onboard implementation of the method.

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Più fonti

Libri sul tema "Orbit method"

1

Duflo, M., M. Vergne, and N. V. Pedersen. The Orbit Method in Representation Theory. Boston, MA: Birkhäuser Boston, 1990. http://dx.doi.org/10.1007/978-1-4612-4486-8.

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National Science Foundation (U.S.), ed. Single orbit dynamics. Providence, RI: American Mathematical Society, 2000.

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3

Duval, Christian, Valentin Ovsienko, and Laurent Guieu, eds. The Orbit Method in Geometry and Physics. Boston, MA: Birkhäuser Boston, 2003. http://dx.doi.org/10.1007/978-1-4612-0029-1.

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4

Gutzwiller, M. C. The motion of the moon as computed by the method of Hill, Brown, and Eckert. Washington: G.P.O., 1986.

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5

Sincarsin, G. B. Geostationary orbital estimation using a Kalman filter. Downsview, Ont: Institute for Aerospace Studies, 1986.

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6

Matching of orbital integrals on GL(4) and GSp(2). Providence, R.I: American Mathematical Society, 1999.

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7

Smith, R. L. Study of a homotopy continuation method for early orbit determination with the tracking and data relay satellite system (TDRSS). [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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8

Babillot, Martine. Rigidité, groupe fondamental et dynamique. Paris: SMF, 2002.

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9

Hypoelliptic laplacian and orbital integrals. Princeton, N.J: Princeton University Press, 2011.

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10

1959-, McGovern William M., ed. Nilpotent orbits in semisimple Lie algebras. New York: Van Nostrand Reinhold, 1993.

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Capitoli di libri sul tema "Orbit method"

1

Fujiwara, Hidenori, and Jean Ludwig. "Orbit Method." In Springer Monographs in Mathematics, 117–66. Tokyo: Springer Japan, 2014. http://dx.doi.org/10.1007/978-4-431-55288-8_5.

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2

Zhang, Yasheng, Yanli Xu, and Haijun Zhou. "Theory and Design Method of Hovering Orbit." In Theory and Design Methods of Special Space Orbits, 37–90. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2948-6_3.

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3

Zhang, Yasheng, Yanli Xu, and Haijun Zhou. "Theory and Design Method of Responsive Orbit." In Theory and Design Methods of Special Space Orbits, 199–223. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2948-6_7.

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4

Kirillov, A. "The orbit method for nilpotent Lie groups." In Graduate Studies in Mathematics, 71–108. Providence, Rhode Island: American Mathematical Society, 2004. http://dx.doi.org/10.1090/gsm/064/03.

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5

Rumberger, Matthias, and Jürgen Scheurle. "The Orbit Space Method: Theory and Application." In Ergodic Theory, Analysis, and Efficient Simulation of Dynamical Systems, 649–89. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-642-56589-2_27.

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6

Corwin, Lawrence. "Towards Harmonic Analysis on Homogeneous Spaces of Nilpotent Lie Groups." In The Orbit Method in Representation Theory, 1–9. Boston, MA: Birkhäuser Boston, 1990. http://dx.doi.org/10.1007/978-1-4612-4486-8_1.

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7

Torasso, Pierre. "The Poisson-Plancherel Formula for a Quasi-Algebraic Group with Abelian Radical and Reductive Generic Stabilizer." In The Orbit Method in Representation Theory, 213–27. Boston, MA: Birkhäuser Boston, 1990. http://dx.doi.org/10.1007/978-1-4612-4486-8_10.

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8

Fujiwara, Hidénori. "Représentations Monomiales des Groupes de Lie Résolubles Exponentiels." In The Orbit Method in Representation Theory, 61–84. Boston, MA: Birkhäuser Boston, 1990. http://dx.doi.org/10.1007/978-1-4612-4486-8_3.

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9

Pukanszky, L. "On a Property of the Quantization Map for the Coadjoint Orbits of Connected Lie Groups." In The Orbit Method in Representation Theory, 187–211. Boston, MA: Birkhäuser Boston, 1990. http://dx.doi.org/10.1007/978-1-4612-4486-8_9.

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Zhang, Yasheng, Yanli Xu, and Haijun Zhou. "Theory and Design Method of Spiral Cruising Orbit." In Theory and Design Methods of Special Space Orbits, 91–137. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2948-6_4.

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Atti di convegni sul tema "Orbit method"

1

Friedman, Aharon, and Eva Bozoki. "Eigenvector method for optimized orbit correction." In Orbit correction and analysis in circular accelerators. AIP, 1994. http://dx.doi.org/10.1063/1.46769.

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2

Tang, Y. N., and S. Krinsky. "Use of regularization method in the determination of ring parameters and orbit correction." In Orbit correction and analysis in circular accelerators. AIP, 1994. http://dx.doi.org/10.1063/1.46776.

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3

Du, Dongmei, and Qing He. "Orbit Shape Automatic Recognition Based on Artificial Neural Network." In ASME 2005 Power Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/pwr2005-50208.

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Orbit is a significant symptom in the fault diagnosis of rotating machine. The orbit is a 2-D image and can be described by moment invariants, the shape property of 2-D image, which is a description with translating-, rotating-, and scaling-invariants for 2-D image. The descriptive method of orbit image is investigated and an automatic orbit shape recognition based on artificial neural network (ANN) with moment invariants is proposed in this paper. The ANN of orbit shape recognition is trained by the training patterns generated by computer simulation for plenty of orbit shapes. It is shown that the trained ANN is of good recognition performance and generalization capability when applied to recognition of the measured orbits. This method can be used to the intelligent expert system of fault diagnosis to obtain automatically online orbit symptom in shafts vibration monitoring of turbine generator, which will improve the automatization of obtaining fault symptom and the automatic diagnosis in the expert system.

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Li, Xiao-Jie, Yong Huang, Rui Guo, Ran-Ran Su, and Kui Geng. "A new dynamic orbit determination method for GEO satellite after orbit maneuver." In 2015 International Conference on Mechanics and Mechatronics (ICMM2015). WORLD SCIENTIFIC, 2015. http://dx.doi.org/10.1142/9789814699143_0105.

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5

Walsh, Matthew T., and Mason A. Peck. "A Method for General Autonomous Orbit Matching." In 2018 AIAA Guidance, Navigation, and Control Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0870.

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6

Ashtari Larki, M. H., M. Maboodi, and H. Bolandi. "Satellite orbit determination based on gradient method." In 2012 24th Chinese Control and Decision Conference (CCDC). IEEE, 2012. http://dx.doi.org/10.1109/ccdc.2012.6244407.

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7

Du, Heng, Boren Du, and Wei Wang. "Neighboring orbit satellite image data conjunction method." In Second International Conference on Image and Graphics, edited by Wei Sui. SPIE, 2002. http://dx.doi.org/10.1117/12.477075.

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KECHICHIAN, JEAN. "An analytic method of orbit determination in near-circular orbit using horizon sensor data." In 28th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-473.

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9

Al-Zamel, Z., and B. F. Feeny. "Improved Estimations of Unstable Periodic Orbits Extracted From Chaotic Sets." In ASME 2001 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/detc2001/vib-21585.

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Abstract Unstable periodic orbits of the saddle type are often extracted from chaotic sets. We use the recurrence method of extracting segments of the chaotic data to approximate the true unstable periodic orbit. Then nearby trajectories are then examined to obtain the dynamics local to the extracted orbit, in terms of an affine map. The affine map is then used to estimate the true orbit. Accuracy is evaluated in examples including well known maps and the Duffing oscillator.

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Jun, Shu, Xu Limin, and Li Jianbing. "An orbit transfer method for spatial object tracking." In 2017 29th Chinese Control And Decision Conference (CCDC). IEEE, 2017. http://dx.doi.org/10.1109/ccdc.2017.7978659.

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Rapporti di organizzazioni sul tema "Orbit method"

1

Parker, B. Novel Method of Compensation of the Effects of Detector Solenoid on the Vertical Beam Orbit in a Linear Collider. Office of Scientific and Technical Information (OSTI), February 2005. http://dx.doi.org/10.2172/839921.

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Chao, Y. C. Orbit Correction Methods - Basic Formulation, Current Applications at Jefferson Lab, and Future Possibilities. Office of Scientific and Technical Information (OSTI), December 1999. http://dx.doi.org/10.2172/754649.

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3

Zilberman, Mark. Methods to Test the “Dimming Effect” Produced by a Decrease in the Number of Photons Received from Receding Light Sources. Intellectual Archive, November 2020. http://dx.doi.org/10.32370/iaj.2437.

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The hypothetical “Dimming Effect” describes the change of the number of photons arriving from a moving light source per unit of time. In non-relativistic systems, the “Dimming effect” may occur due to the growing distance of light sources moving away from the receiver. This means that due to the growing distance, the photons continuously require more time to reach the receiver, which reduces the number of received photons per time unit compared to the number of emitted photons. Understandably, the proposed “Dimming effect” must be tested (confirmed or rejected) through observations. a. This article provides the formula for the calculation of “Dimming effect” values using the redshift parameter Z widely used in astronomy. b. The “Dimming effect” can possibly be detected utilizing the orbital movement of the Earth around the Sun. In accordance to the “Dimming effect”, observers on Earth will view 1.0001 more photons per time unit emitted by stars located near the ecliptic plane in the direction of the Earth orbiting the Sun. And, in contrast, observers will view only 0.9999 photons per time unit emitted by stars located near the ecliptic plane in the direction opposite to the Earth orbiting the Sun. Calculating precise measurements of the same stars within a 6-month period can possibly detect this difference. These changes in brightness are not only for specific stars, as the change in brightness takes place for all stars near the ecliptic in the direction of the Earth’s orbit around the Sun and in the opposite direction. c. The “Dimming effect” can possibly be detected in a physics laboratory using a moving light source (or mirror) and photon counters located in the direction of travel and in the opposite direction. d. In theory, Dilation of time can also be used for testing the existence of the “Dimming effect.” However, in experiments on Earth this effect appears in only the 14th digit after the decimal point and testing does not appear to be feasible. e. Why is it important to test the “Dimming effect?” If confirmed, it would allow astronomers to adjust values of "Standard Candles" used in astronomy. Since “Standard Candles” are critical in various cosmological models, the “Dimming effect” can correct models and/or reveal and support new models. If it is proved that the “Dimming effect” does not exist, it will mean that the number of photons arriving per unit of time does not depend on the speed of the light source and observer, which is not so apparent.

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