標(biāo)題: Titlebook: Celestial Mechanics and Astrodynamics: Theory and Practice; Pini Gurfil,P. Kenneth Seidelmann Book 2016 Springer-Verlag GmbH Germany, part [打印本頁(yè)] 作者: Taft 時(shí)間: 2025-3-21 16:05
書(shū)目名稱Celestial Mechanics and Astrodynamics: Theory and Practice影響因子(影響力)
書(shū)目名稱Celestial Mechanics and Astrodynamics: Theory and Practice影響因子(影響力)學(xué)科排名
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書(shū)目名稱Celestial Mechanics and Astrodynamics: Theory and Practice網(wǎng)絡(luò)公開(kāi)度學(xué)科排名
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書(shū)目名稱Celestial Mechanics and Astrodynamics: Theory and Practice讀者反饋
書(shū)目名稱Celestial Mechanics and Astrodynamics: Theory and Practice讀者反饋學(xué)科排名
作者: carotid-bruit 時(shí)間: 2025-3-21 23:51 作者: 大笑 時(shí)間: 2025-3-22 03:12 作者: 1FAWN 時(shí)間: 2025-3-22 08:15 作者: 苦笑 時(shí)間: 2025-3-22 11:29 作者: SYN 時(shí)間: 2025-3-22 13:13 作者: SYN 時(shí)間: 2025-3-22 18:00 作者: 打擊 時(shí)間: 2025-3-23 01:15 作者: 苦澀 時(shí)間: 2025-3-23 02:49 作者: Occipital-Lobe 時(shí)間: 2025-3-23 07:01
Orale implantaten in de algemene praktijkbject of many studies over the years. Because the dynamics in this case are generally ., and might even exhibit chaos (Celletti and Negrini 1995; Irigoyen and Simo 1993), as discussed in Sects. 1.5 and 1.6, the only possible closed-form solutions may be obtained by approximating and/or averaging the .. gravitational potential.作者: Truculent 時(shí)間: 2025-3-23 11:15
Orale implantaten in de algemene praktijktrol laws also utilize mean orbital elements. The . are most commonly defined as doubly-averaged elements, obtained from a doubly-averaged Hamiltonian. However, the mean elements in the current chapter will be singly-averaged elements, obtained by removing the short-periodic oscillations only.作者: PAC 時(shí)間: 2025-3-23 16:03
Motion Around Oblate Planets,bject of many studies over the years. Because the dynamics in this case are generally ., and might even exhibit chaos (Celletti and Negrini 1995; Irigoyen and Simo 1993), as discussed in Sects. 1.5 and 1.6, the only possible closed-form solutions may be obtained by approximating and/or averaging the .. gravitational potential.作者: 嘲弄 時(shí)間: 2025-3-23 21:19
Semianalytical Orbit Theory,trol laws also utilize mean orbital elements. The . are most commonly defined as doubly-averaged elements, obtained from a doubly-averaged Hamiltonian. However, the mean elements in the current chapter will be singly-averaged elements, obtained by removing the short-periodic oscillations only.作者: 可耕種 時(shí)間: 2025-3-23 23:19
Wat is het beloop zonder behandeling?,let us consider the other problem: Given the observations of an object, determine the elements of its orbit. We have considered determining the elements when the position and velocity are known, but these are not the usual observations. Radar observations can give the radial distance. Doppler observ作者: 印第安人 時(shí)間: 2025-3-24 06:08 作者: 人造 時(shí)間: 2025-3-24 06:45 作者: 玩忽職守 時(shí)間: 2025-3-24 13:46 作者: 廚房里面 時(shí)間: 2025-3-24 17:15
Orale implantaten in de algemene praktijklate, and thereby comprehend, the orbital dynamics of satellites. In many cases of practical interest, as we will see in Chap. 14, satellite orbit control laws also utilize mean orbital elements. The . are most commonly defined as doubly-averaged elements, obtained from a doubly-averaged Hamiltonian作者: 含沙射影 時(shí)間: 2025-3-24 22:55
G. M. Raghoebar,R. J. Goené,A. Vissinker problem is the fuel-optimal impulsive transfer between 2 coplanar circular orbits. Three such transfers are the Hohmann transfer, discussed in Sect. 14.7.1; the .; and the .. These transfers were originally conceived based on the Keplerian two-body problem, discussed in Chap. 5作者: 閑蕩 時(shí)間: 2025-3-24 23:18
4a Addendum: Mediaal tibiaal stresssyndroom,tial mechanics and astrodynamics. These include the processing and filtering of observations and fitting ephemerides to the observations, determining an approximation for a given set of measurements, the use of polynomials for the computation from numerical integrations of positions of objects for s作者: 只有 時(shí)間: 2025-3-25 06:17 作者: obscurity 時(shí)間: 2025-3-25 10:00
https://doi.org/10.1007/978-3-662-50370-6Atmospheric Drag; Canonical Transformations; Celestial Mechanics and Astrodynamics; Computation of Orbi作者: seruting 時(shí)間: 2025-3-25 13:22 作者: 命令變成大炮 時(shí)間: 2025-3-25 18:18 作者: brachial-plexus 時(shí)間: 2025-3-25 23:34
Astrophysics and Space Science Libraryhttp://image.papertrans.cn/c/image/222719.jpg作者: 自負(fù)的人 時(shí)間: 2025-3-26 02:58
Celestial Mechanics and Astrodynamics: Theory and Practice978-3-662-50370-6Series ISSN 0067-0057 Series E-ISSN 2214-7985 作者: JOT 時(shí)間: 2025-3-26 07:17 作者: 自傳 時(shí)間: 2025-3-26 08:49
10 Afwijkingen van het hoornvliesNo theoretical developments will be presented; for theory the reader might consult a work on finite differences. The notation to be used and reference to more information is available from Nautical Almanac Office (.).作者: 苦笑 時(shí)間: 2025-3-26 15:28 作者: Brain-Waves 時(shí)間: 2025-3-26 20:18 作者: Coronary 時(shí)間: 2025-3-26 23:52 作者: FLINT 時(shí)間: 2025-3-27 02:12
Behandelingstechnieken in de orthopedieThis chapter is meant to provide the basic information concerning vectors, hopefully as a review, but to ensure that the reader is familiar with the basics.作者: artless 時(shí)間: 2025-3-27 07:37
Behandelingstechnieken in de orthopedieA reference system is a theoretical concept of coordinates, and includes the time and the standards necessary to specify the bases for giving positions and motions in the system. There are celestial and terrestrial reference systems作者: dialect 時(shí)間: 2025-3-27 12:51 作者: 虛假 時(shí)間: 2025-3-27 15:39
https://doi.org/10.1007/978-90-313-6549-4Assume that the masses are spherically symmetrical and homogeneous in concentric layers. So they attract one another as if the mass were concentrated at spherical centers作者: 巨大沒(méi)有 時(shí)間: 2025-3-27 19:18
https://doi.org/10.1007/978-90-313-6558-6An important particular solution of the three-body problem results when one of the three masses is so small, in comparison to the other two, that its gravitational effects can be neglected. This may be called an . compared with the two finite bodies. This is the restricted three-body problem (Szebehely .), as mentioned in Sect. 1.5作者: 拉開(kāi)這車床 時(shí)間: 2025-3-28 00:40
10 Afwijkingen van het hoornvliesNow we want to look at a completely different approach to solving the equations of motion, and a different type of variables. We must first establish our notation and the equations of motion which underlie this approach.作者: Choreography 時(shí)間: 2025-3-28 05:29 作者: 都相信我的話 時(shí)間: 2025-3-28 09:50
Orale implantaten in de algemene praktijkSatellite orbit control refers to the process of generating thrust for tracking a particular orbit in the presence of orbital perturbations. The particular orbit is mission dependent. It could be a low Earth orbit (LEO), used for Earth imaging, a geostationary orbit (GEO) used for communication and weather monitoring, or an interplanetary orbit.作者: encomiast 時(shí)間: 2025-3-28 13:35 作者: 生存環(huán)境 時(shí)間: 2025-3-28 17:34
Introduction,Celestial mechanics embraces the dynamical and mathematical theories describing the motions of planets, satellites, one member of a double star pair around another, and similar phenomena.作者: 感情 時(shí)間: 2025-3-28 21:57 作者: progestin 時(shí)間: 2025-3-28 23:27 作者: 感情 時(shí)間: 2025-3-29 04:33 作者: 歪曲道理 時(shí)間: 2025-3-29 07:43
The Two-Body Problem,Assume that the masses are spherically symmetrical and homogeneous in concentric layers. So they attract one another as if the mass were concentrated at spherical centers作者: Kidnap 時(shí)間: 2025-3-29 14:43
The Restricted Three-Body Problem,An important particular solution of the three-body problem results when one of the three masses is so small, in comparison to the other two, that its gravitational effects can be neglected. This may be called an . compared with the two finite bodies. This is the restricted three-body problem (Szebehely .), as mentioned in Sect. 1.5作者: Cougar 時(shí)間: 2025-3-29 18:52 作者: Interstellar 時(shí)間: 2025-3-29 20:28
General Perturbations Theory,We have seen the complexity of the problem when more than two gravitating masses are involved. We have seen two methods of determining the orbits, Cowell’s and Encke’s methods. Now, let us look at the basic mathematical description of the perturbation problem.作者: 過(guò)渡時(shí)期 時(shí)間: 2025-3-30 03:12 作者: Paraplegia 時(shí)間: 2025-3-30 05:22
People, Progress, Prospects,The developments and progress in celestial mechanics and astrodynamics can in most cases be tied directly to the scientists who contributed to the ideas and advancements. Some of those people are identified here.作者: 水土 時(shí)間: 2025-3-30 09:58
The n-Body Problem,n be mathematically formulated so a closed-form solution is possible. With more than two bodies, it is impossible to formulate such a solution. There are some special cases, however, that can be handled.作者: 翅膀拍動(dòng) 時(shí)間: 2025-3-30 15:31 作者: leniency 時(shí)間: 2025-3-30 20:17 作者: Magnitude 時(shí)間: 2025-3-30 21:44 作者: countenance 時(shí)間: 2025-3-31 01:38
Orbit Determination,let us consider the other problem: Given the observations of an object, determine the elements of its orbit. We have considered determining the elements when the position and velocity are known, but these are not the usual observations. Radar observations can give the radial distance. Doppler observ作者: 色情 時(shí)間: 2025-3-31 06:12
The n-Body Problem,n be mathematically formulated so a closed-form solution is possible. With more than two bodies, it is impossible to formulate such a solution. There are some special cases, however, that can be handled.作者: 恃強(qiáng)凌弱的人 時(shí)間: 2025-3-31 10:38
Numerical Procedures,No theoretical developments will be presented; for theory the reader might consult a work on finite differences. The notation to be used and reference to more information is available from Nautical Almanac Office (.).作者: 爆炸 時(shí)間: 2025-3-31 17:13 作者: etidronate 時(shí)間: 2025-3-31 19:42
