BOOST
发表于 2025-3-23 12:24:03
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extemporaneous
发表于 2025-3-23 14:02:11
Orbital Relative Motion and Terminal Rendezvous978-3-030-64657-8Series ISSN 0924-4263 Series E-ISSN 2542-8896
OCTO
发表于 2025-3-23 18:21:19
Book 2021ives. The first is to derive the mathematics of relative motion in near-circular orbit when subjected to perturbations emanating from the oblateness of the Earth, third-body gravity, and atmospheric drag. The mathematics are suitable for quick trajectory prediction and the creation of computer codes
喃喃诉苦
发表于 2025-3-23 22:18:29
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critique
发表于 2025-3-24 02:21:57
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cogent
发表于 2025-3-24 08:57:24
Analytic Solutions for the Perturbed Motion of a Spacecraft in Near-Circular Orbit, Under the Influthe . harmonic, a position error of 200 m per revolution is sustained when the initial orbit is circular. The equations developed in this chapter can be used to carry out terminal rendezvous in near-circular obit around the oblate Earth.
cloture
发表于 2025-3-24 14:12:37
The Analysis of the Relative Motion in General Elliptic Orbit with Respect to a Dragging and Precese equations can be effectively put to use in calculating by an iterative scheme, the impulsive rendezvous maneuvers in elliptic orbit around the Earth or those planets that are either atmosphere bearing or have a dominant second zonal harmonic, or both.
爱了吗
发表于 2025-3-24 16:39:59
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阻挠
发表于 2025-3-24 21:48:17
Effect of Luni-Solar Gravity Perturbations on a Near-Circular Orbit: Third-Body Orbit Eccentricity ied out, all the orbital elements can be readily obtained and used for example in the maneuver planning function. This theory can be useful for the autonomous navigation of geostationary spacecraft as well as other high near-circular orbit applications such as the GPS spacecraft.
consolidate
发表于 2025-3-25 03:03:43
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