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001469927 001__ 1469927
001469927 003__ OCoLC
001469927 005__ 20230803003353.0
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001469927 019__ $$a1385290082$$a1385454941
001469927 020__ $$a9789811948398$$q(electronic bk.)
001469927 020__ $$a9811948399$$q(electronic bk.)
001469927 020__ $$z9789811948381
001469927 020__ $$z9811948380
001469927 0247_ $$a10.1007/978-981-19-4839-8$$2doi
001469927 035__ $$aSP(OCoLC)1385451843
001469927 040__ $$aEBLCP$$beng$$cEBLCP$$dGW5XE$$dYDX$$dOCLCF
001469927 0411_ $$aeng$$hchi
001469927 049__ $$aISEA
001469927 050_4 $$aTL1075
001469927 08204 $$a629.41015118$$223/eng/20230629
001469927 1001_ $$aLiu, Lin.
001469927 24510 $$aAlgorithms for satellite orbital dynamics /$$cLin Liu.
001469927 260__ $$aSingapore :$$bSpringer,$$c2023.
001469927 300__ $$a1 online resource (576 p.).
001469927 336__ $$atext$$btxt$$2rdacontent
001469927 337__ $$acomputer$$bc$$2rdamedia
001469927 338__ $$aonline resource$$bcr$$2rdacarrier
001469927 4901_ $$aSpringer series in astrophysics and cosmology
001469927 500__ $$a2.3 Expansions of Variables in the Elliptical Orbital Motion
001469927 504__ $$aIncludes bibliographical references.
001469927 5050_ $$aIntro -- Preface -- Introduction -- Orbital Dynamics in the Solar System -- Two Dynamical Systems in the Orbital Dynamics -- Mathematical Models for Satellite Motion: The Perturbed Two-Body Problem [1-8] -- The Two-Body Problem and Kepler Orbit -- The Method of Solving the Perturbed Two-Body Problem -- The Perturbed Restricted Three-Body Problem in the Motion of Deep-Space Prober -- The Restricted Three-Body Problem for Circular and Elliptical Motions [9-12] -- Models for the Restricted N-body Problem and the Perturbed Restricted Three-Body Problem [13, 14]
001469927 5058_ $$aThe Restricted Problem of (n + k)-Bodies [15, 16] -- General Restricted Three-Body Problem -- References -- Contents -- About the Author -- 1 Selections and Transformations of Coordinate Systems -- 1.1 Time Systems and Julian Day [1, 2] -- 1.1.1 Selection of Standard Time -- 1.1.2 Time Reference Systems -- 1.1.3 Julian Day -- 1.2 Space Coordinate Systems [2-6] -- 1.3 Earth's Coordinate Systems [2, 6-10] -- 1.3.1 The Realization of the Dynamical Reference System and J2000.0 Mean Equatorial Reference System -- 1.3.2 The Intermediate Equator and Three Related Datum Points
001469927 5058_ $$a1.3.3 Three Geocentric Coordinate Systems -- 1.3.4 Transformation of the Earth-Fixed Coordinate System O-XYZ and the Geocentric Celestial Coordinate System O-xyz -- 1.3.5 Relationship Between the IAU 1980 Model and the IAU 2000 Model -- 1.3.6 The Complicity in the Selection of Coordinate System Due to the Wobble of Earth's Equator -- 1.3.7 Coordinate Systems Related to Satellite Measurements, Attitudes, and Orbital Errors -- 1.4 The Moon's Coordinate Systems -- 1.4.1 Definitions of the Three Selenocentric Coordinate Systems [6] -- 1.4.2 The Moon's Physical Libration
001469927 5058_ $$a1.4.3 Transformations Between the Three Selenocentric Coordinate Systems -- 1.5 Planets' Coordinate Systems -- 1.5.1 Definitions of Three Mars-Centric Coordinate Systems -- 1.5.2 Mars's Precession Matrix -- 1.5.3 Transformation of the Mars-Centric Equatorial Coordinate System and the Mars-Fixed Coordinate System -- 1.5.4 Transformation of the Geocentric Coordinate System and the Mars-Centric Coordinate System -- 1.5.5 An Explanation of the Application of the IAU 2000 Orientation Models of Celestial Bodies -- References -- 2 The Complete Solution for the Two-Body Problem
001469927 5058_ $$a2.1 Six Integrals of the Two-Body Problem -- 2.1.1 The Angular Momentum Integral (the Areal Integral) -- 2.1.2 The Orbital Integral in the Motion Plane and the Vis Viva Formula -- 2.1.3 The Sixth Motion Integral: Kepler's Equation -- 2.2 Basic Formulas of the Elliptical Orbital Motion -- 2.2.1 Geometric Relationships of the Orbital Elements in the Elliptical Motion -- 2.2.2 Expressions of the Position Vector ""0245r and Velocity -- 2.2.3 Partial Derivatives of Some Variables with Respect to Orbital Elements -- 2.2.4 Derivatives of M, E, and F with Respect to Time t
001469927 506__ $$aAccess limited to authorized users.
001469927 520__ $$aThis book highlights the fundamental physics of orbit theory, dynamical models, methods of orbit determination, design, measurement, adjustment, and complete calculations for the position, tracking, and prediction of satellites and deep spacecraft. It emphasizes specific methods, related mathematical calculations, and worked examples and exercises. Therefore, technicians and engineers in the aerospace industry can directly apply them to their practical work. Dedicated to undergraduate students and graduate students, researchers, and professionals in astronomy, physics, space science, and related aerospace industries, the book is an integrated work based on the accumulated knowledge in satellite orbit dynamics and the authors more than five decades of personal research and teaching experience in astronomy and aerospace dynamics.
001469927 588__ $$aOnline resource; title from PDF title page (SpringerLink, viewed June 29, 2023).
001469927 650_0 $$aSpace trajectories$$xMathematical models.
001469927 650_0 $$aAlgorithms.
001469927 655_0 $$aElectronic books.
001469927 7001_ $$aZhang, Shengpan.
001469927 77608 $$iPrint version:$$aLiu, Lin$$tAlgorithms for Satellite Orbital Dynamics$$dSingapore : Springer,c2023$$z9789811948381
001469927 830_0 $$aSpringer series in astrophysics and cosmology.
001469927 852__ $$bebk
001469927 85640 $$3Springer Nature$$uhttps://univsouthin.idm.oclc.org/login?url=https://link.springer.com/10.1007/978-981-19-4839-8$$zOnline Access$$91397441.1
001469927 909CO $$ooai:library.usi.edu:1469927$$pGLOBAL_SET
001469927 980__ $$aBIB
001469927 980__ $$aEBOOK
001469927 982__ $$aEbook
001469927 983__ $$aOnline
001469927 994__ $$a92$$bISE