排序方式: 共有4条查询结果,搜索用时 15 毫秒
1
1.
F.J.T. Salazar E.E.N. Macau O.C. Winter 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
Lagrangian points L4 and L5 lie at 60° ahead of and behind the Moon in its orbit with respect to the Earth. Each one of them is a third point of an equilateral triangle with the base of the line defined by those two bodies. These Lagrangian points are stable for the Earth–Moon mass ratio. As so, these Lagrangian points represent remarkable positions to host astronomical observatories or space stations. However, this same distance characteristic may be a challenge for periodic servicing mission. This paper studies elliptic trajectories from an Earth circular parking orbit to reach the Moon’s sphere of influence and apply a swing-by maneuver in order to re-direct the path of a spacecraft to a vicinity of the Lagrangian points L4 and L5. Once the geocentric transfer orbit and the initial impulsive thrust have been determined, the goal is to establish the angle at which the geocentric trajectory crosses the lunar sphere of influence in such a way that when the spacecraft leaves the Moon’s gravitational field, its trajectory and velocity with respect to the Earth change in order to the spacecraft arrives at L4 and L5. In this work, the planar Circular Restricted Three Body Problem approximation is used and in order to avoid solving a two boundary problem, the patched-conic approximation is considered. 相似文献
2.
The information on the project being developed in Brazil for a flight to binary or triple near-Earth asteroid is presented.
The project plans to launch a spacecraft into an orbit around the asteroid and to study the asteroid and its satellite within
six months. Main attention is concentrated on the analysis of trajectories of flight to asteroids with both impulsive and
low thrust in the period 2013-2020. For comparison, the characteristics of flights to the (45) Eugenia triple asteroid of
the Main Belt are also given. 相似文献
3.
Chian A.C.-L. Borotto F.A. Rempel E.L. Macau E.E.N. Rosa R.R. Christiansen F. 《Space Science Reviews》2003,107(1-2):447-461
Space plasmas are dominated by waves, instabilities and turbulence. Dynamical systems approach offers powerful mathematical
and computational techniques to probe the origin and nature of space environment turbulence. Using the nonlinear dynamics
tools such as the bifurcation diagram and Poincaré maps, we study the transition from order to chaos, from weak to strong
chaos, and the destruction of a chaotic attractor. The characterization of the complex system dynamics of the space environment,
such as the Alfvén turbulence, can improve the capability of monitoring Sun-Earth connections and prediction of space weather.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
4.
F.J.T. Salazar J.J. Masdemont G. Gómez E.E. Macau O.C. Winter 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
Assume a constellation of satellites is flying near a given nominal trajectory around L4 or L5 in the Earth–Moon system in such a way that there is some freedom in the selection of the geometry of the constellation. We are interested in avoiding large variations of the mutual distances between spacecraft. In this case, the existence of regions of zero and minimum relative radial acceleration with respect to the nominal trajectory will prevent from the expansion or contraction of the constellation. In the other case, the existence of regions of maximum relative radial acceleration with respect to the nominal trajectory will produce a larger expansion and contraction of the constellation. The goal of this paper is to study these regions in the scenario of the Circular Restricted Three Body Problem by means of a linearization of the equations of motion relative to the periodic orbits around L4 or L5. This study corresponds to a preliminar planar formation flight dynamics about triangular libration points in the Earth–Moon system. Additionally, the cost estimate to maintain the constellation in the regions of zero and minimum relative radial acceleration or keeping a rigid configuration is computed with the use of the residual acceleration concept. At the end, the results are compared with the dynamical behavior of the deviation of the constellation from a periodic orbit. 相似文献
1