Loading...
Search for:
halo-orbits
0.005 seconds
Optimal Transfer Trajectory Design to Halo Orbits Using Homotopy Approach
, M.Sc. Thesis Sharif University of Technology ; Pourtakdoust, Hossein (Supervisor) ; Kiani, Maryam (Supervisor)
Abstract
Optimal Maneuvering to lessen the required fuel or to speed up the mission operation time is a significant part of various space missions. Optimal performance of a spacecraft reduces the mission cost, increases the mission life time and subsequently provides more chances for space exploration. In this sense, optimal maneuvering has always been at the center of attention and abundant works have been assigned to this importance. This research is also devoted to optimal trajectory design to transfer from low Earth orbits to the halo orbits. Specific characteristics of the halo orbits including periodicity, geometry, and particular position around the collinear liberation points of the...
Linear and nonlinear control strategies for formation and station keeping of spacecrafts within the context of the three body problem
, Article Aerospace Science and Technology ; Volume 42 , December , 2015 , Pages 12-24 ; 12709638 (ISSN) ; Pourtakdoust, S. H ; Assadian, N ; Sharif University of Technology
Elsevier Masson SAS
2015
Abstract
The problem of spacecraftformation control and reconfiguration for halo orbit around the second libration point (L2) of the Sun-Earth Three Body (TB) system is investigated. Station keeping, reconfigu-ration and precision formation control of spacecrafts on halo orbits are performed via the use of the nonlinear Integral Sliding Mode (ISM) method as well as the optimal closed loop Linear Quadratic Regulator(LQR) approach. In this regard the nonlinear relative dynamics of deputy-chief spacecrafts are derived within the concept of the three body problem. The behavior of the two controllers are compared for different tasks of the formation mission in order to determine the more preferred...
MPC Control of Satellite Formation in the Context of Three Body Problem
, M.Sc. Thesis Sharif University of Technology ; Pourtakdoust, Hossein (Supervisor)
Abstract
In this thesis the problem of spacecrafts formation control for halo orbit around the second libration point (L2) of the Sun-Earth Three Body (TB) system is investigated. Station keeping, reconfiguration and precision formation control of spacecrafts on halo orbits are performed via the use of the nonlinear Integral Sliding Mode (ISM) method, optimal closed loop Linear Quadratic regulator (LQR) approach as well as the Model Prodective Control (MPC). In this regard the nonlinear relative dynamics of deputy-chief spacecrafts are derived within the concept of both circular and elliptical three body problem; as well the perturbation model of the Moon and the linear model of restricted three...
Reconfiguration of Multiple Spacecraftsfor Deflecting an Asteroid with Gravity Tractor Method
, M.Sc. Thesis Sharif University of Technology ; Pourtakdoust, Hossein (Supervisor)
Abstract
In this work the problem of optimal spacecrafts reconfiguration and formation keeping is investigated for Asteroid attraction. Due to potential impact probability of the Apophis asteroid with Earth in 2036, the study is focused on optimal intercept avoidance via gravity attraction of multiple spacecrafts suitably arranged on halo orbits of Apophis. In this regard, a space mission is defined in which initially several spacecrafts are optimally reconfigured onspecial Halo orbits of the asteroid via several techniques that include pseudospectral, linear quadratic regulator as well as the integral sliding mode control. The utility of three methods is for verification purposes as well as...