Solar radiation pressure and deviations from Keplerian orbits
نویسندگان
چکیده
منابع مشابه
Osculating Keplerian Elements for Highly Non- Keplerian Orbits
There may be differences between this version and the published version. You are advised to consult the publisher's version if you wish to cite from it. This paper presents a mapping between the elements of highly non-Keplerian orbits and classical orbital elements. Three sets of elements are discussed and mappings are derived in closed, analytical form for both the direct and inverse problem. ...
متن کاملLyapunov-based Transfer between Elliptic Keplerian Orbits
We present a study of the transfer of satellites between elliptic Keplerian orbits using Lyapunov stability theory specific to this problem. The construction of Lyapunov functions is based on the fact that a non-degenerate Keplerian orbit is uniquely described by its angular momentum and Laplace (Runge-Lenz) vectors. We suggest a Lyapunov function, which gives a feedback controller such that th...
متن کاملGeometric optimal control of elliptic Keplerian orbits
This article deals with the transfer of a satellite between Keplerian orbits. We study the controllability properties of the system and make a preliminary analysis of the time optimal control using the maximum principle. Second order sufficient conditions are also given. Finally, the time optimal trajectory to transfer the system from an initial low orbit with large eccentricity to a terminal g...
متن کاملDirect solar radiation pressure on the orbits of small near–Earth asteroids: observable effects?
We consider the perturbations of Near–Earth Asteroid orbits due to direct solar radiation pressure (both the absorption and the reflection components). When the body is spherical and the surface albedo homogeneous the effect is small (and only short–periodic). However, when at least one of these restrictive and unrealistic assumptions is relaxed, long–term orbital effects appear and they may po...
متن کاملOrbital Perturbation Effect on LEO Satellite Trajectory
A satellite, in its orbit, is affected by perturbing forces, such as atmospheric drag, solar radiation pressure, Earth oblateness, and gravity of the celestial masses (other than the Earth). In this paper, the effects of these forces on the trajectories of different types of LEO satellites and a sample satellite (Z-SAT) are discussed. A few analyses are done on these orbits and the relevant res...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Physics Letters B
سال: 2009
ISSN: 0370-2693
DOI: 10.1016/j.physletb.2009.03.058