Search for: orbits
Total 214 records
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
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...
Article Physics Letters, Section A: General, Atomic and Solid State Physics ; Volume 374, Issue 36 , August , 2010 , Pages 3793-3796 ; 03759601 (ISSN) ; Jafari, S. A ; Sharif University of Technology
Remarkable inter-band nesting in FeO Fermi surface, hints to examine energy of orbitally ordered states, which turn out to be more stable. We propose this method as a general scheme to check for possibility of orbital ordering in first principle calculations, and demonstrate it for known examples, LiVO2 and LaMnO3
Article Advances in Space Research ; Volume 66, Issue 4 , 2020 , Pages 992-1000 ; Pourtakdoust, S. H ; Sayanjali, M ; Sharif University of Technology
Elsevier Ltd 2020
This paper proposes a solution for multiple-impulse orbital maneuvers near circular orbits for special cases where orbital observations are not globally available and the spacecraft is being observed through a limited window from a ground or a space-based station. The current study is particularly useful for small private launching companies with limited access to global observations around the Earth and for orbital maneuvers around other planets for which the orbital observations are limited to the in situ equipment. An appropriate cost function is introduced for the sake of minimizing the total control/impulse effort as well as the orbital uncertainty. It is subsequently proved that for a...
Article Inorganic Chemistry ; 2021 ; 00201669 (ISSN) ; Jamali, S ; Mahmoudi, S ; Samouei, H ; Nayeri, S ; Chabok, S. M. J ; Jamshidi, Z ; Sharif University of Technology
American Chemical Society 2021
Herein we describe the synthesis and characterization of the first platinum(IV) metal-organic cage [(Me3PtIV)8(byp)12](OTf)8 (2), in which the organometallic moieties trimethylplatinum(IV) (PtMe3) occupied the corners of a cubane structure and 4,4′-bipyridine ligands used as linkers. The first-principles density functional theory calculations showed that the highest occupied molecular orbitals were localized on the PtMe3 moieties, while the lowest unoccupied molecular orbitals were distributed on the organic linkers. © 2021 American Chemical Society
M.Sc. Thesis Sharif University of Technology ; Pourtakdoust, Hossein
Orbit perturbations are most important environmental factors that affecting performance of satellites. These effects mainly in two ways affect the satellite. Through the first, perturbing acceleration, change the orbital elements and the second, moments due to perturbations, couple the dynamics and attitude equations. Various studies regarding how the resources of major perturbations such as direct solar radiation, atmosphere and the third body attractions have been done. However, effects a significant number of other perturbations, such as solar, rotation of the atmosphere, reflected solar radiations, earth oblateness with high order of earth harmonics consideration and small forces (such...
Article Iranian Journal of Science and Technology - Transactions of Mechanical Engineering ; Volume 36, Issue M1 , 2012 , Pages 83-93 ; 22286187 (ISSN) ; Zohoor, H ; Sohrabpour, S ; Sharif University of Technology
Finding special periodic orbit in the highly chaotic problems is very complicated. Thus, deriving an effective algorithm for finding such orbits is important. In this paper, the spatial orbits in three-body problems are studied. Then, an algorithm is derived in order to help to find these orbits. This algorithm includes scanning the space, refining better points, and finally, minimizing the position error of the orbit by means of numerical methods
Article Acta Astronautica ; Volume 161 , 2019 , Pages 200-208 ; 00945765 (ISSN) ; Kiani, M ; Pourtakdoust, S. H ; Sharif University of Technology
Elsevier Ltd 2019
A new shape-based geometric method (SBGM) is proposed for generation of multi-impulse transfer trajectories between arbitrary coplanar oblique orbits via a heuristic algorithm. The key advantage of the proposed SBGM includes a significant reduction in the number of design variables for an N-impulse orbital maneuver leading to a lower computational effort and energy requirement. The SBGM generates a smooth transfer trajectory by joining a number of confocal elliptic arcs such that the intersections share common tangent directions. It is proven that the well-known classic Hohmann transfer and its bi-elliptic counterpart between circular orbits are special cases of the proposed SBGM. The...
Article Manchester Microlensing Conference, M2C: 12th International Conference on Gravitational Microlensing, and ANGLES Microlensing Workshop, GMC 2008, 21 January 2008 through 25 January 2008 ; Volume 54 , 2008 ; 18248039 (ISSN) ; Dominik, M ; Sharif University of Technology
Sissa Medialab Srl 2008
One of the successful techniques for the detection of exoplanets relies on the magnification of an observed star resulting from microlensing by a foreground star orbited by a planetary companion. We propose an alternative method for the detection of exoplanets by microlensing, in which the orbital motion of a planet around the source star induces a small motion of the star around the common barycentre, which leads to detectable deviations from the ordinary symmetric microlensing light curve. We show that favourable events for such deviations to occur involve lenses close to the source star and Einstein-radius crossing times substantially larger than the planet’s orbital period. From a...
Article International Journal of Structural Stability and Dynamics ; Volume 13, Issue 4 , 2013 ; 02194554 (ISSN) ; Malaek, S. M ; Sharif University of Technology
The loads induced on the spacecraft orbiting the Earth by the deploying elastic arm are investigated. The coupled equations of motion of the arm with the vehicle orbital mechanics are used to describe the 3D dynamic behavior of the flexible-appendage and the related disturbing loads induced on the spacecraft. To this end, an equivalent dynamical system is derived for the arm by applying an attached Non-Newtonian Reference Frame which is subjected to the orbital motion and geocentric pointing maneuver of the spacecraft. With the help of the Assumed Modes Method, the behavior of the arm attached to the spacecraft in Keplerian orbits is studied. The results show that deploying the arm in some...
Article International Journal of Dynamics and Control ; Volume 5, Issue 3 , 2017 , Pages 741-755 ; 2195268X (ISSN) ; Saghafi, F ; Pasand, M ; Sharif University of Technology
Recent developments in the space industry and the great tendency to define efficient, precise and low cost missions are the main reasons for the growing interest in satellites formation flight. Regarding the aforementioned, the study of multiple satellites control methods is the subject of the present paper. In this paper, two linear robust control strategies are applied to position control system of certain satellites in the virtual structure formation flight. The proposed controllers are designed considering different parametric uncertainties such as semimajor axis and eccentricity changes as well as some disturbances like second term of gravitational acceleration function (j2) and drag...
Ph.D. Dissertation Sharif University of Technology ; Zohoor, Hassan ; Sohrabpour, Saeed
Periodic orbits in a three-body problem are important issues. These orbits are mostly unstable. The Main reason of this instability is the second mass gravity. So, these orbits are deviated from Keplerian orbits. Besides, controlling a spaceship in these orbits is an important issue. In this research stability of these orbits are studied. We used Flouquet and Lyuponov exponents for measuring the instability. We introduced a new method for double Poincare map, as well. These maps can show the system changes in state space. In addition to above we introduced an algorithm that can reduce the time of periodic orbit finding. The conventional and unconventional control methods for stabilizing a...
M.Sc. Thesis Sharif University of Technology ; Pourtakdoust, Hossien
Nowadays there are various means in the field of orbital mechanics used in different levels and their accuracy depends on the theory and complexity of the governing equations used in their development. Most of them just simulate the motion of an orbiting satellite while there exist some commercial products able to provide the user with the orbital performance specifications and almost none of them have a module to design an orbit, based on a required performance such as specific coverage / ground track, shadow/light duration, etc .... Although satisfying performance requirements and a set of orbital elements simultaneously only seems to be possible for some particular orbits, there is an...
Article Scientia Iranica ; Volume 18, Issue 3 B , 2011 , Pages 393-397 ; 10263098 (ISSN) ; Zohoor, H ; Sohrabpour, S ; Sharif University of Technology
Priodic orbits have been studied more extensively by space mission designers in recent years. These orbits are usually described as planar in three-body-problems. In this article, in addition to introducing a new orbit that turns around a secondary mass, applications in Moon-based, Earth-based, and interplanetary missions are also described. Floquet exponents as chaos indicators and normal potential levels for orbits are also calculated. The advantages of their use as space station orbits are studied at the end of the article
Article Advances in Space Research ; Volume 55, Issue 4 , 2015 , Pages 1028-1037 ; 02731177 (ISSN) ; Pourtakdoust, S. H ; Sharif University of Technology
Elsevier Ltd 2015
Accurate orbit determination (OD) is vital for every space mission. This paper proposes a novel heuristic filter based on adaptive sample-size Gaussian swarm optimization (AGSF). The proposed estimator considers the OD as a stochastic dynamic optimization problem that utilizes a swarm of particles in order to find the best estimation at every time step. One of the key contributions of this paper is the adaptation of the swarm size using a weighted variance approach. The proposed strategy is simulated for a low Earth orbit (LEO) OD problem utilizing geomagnetic field measurements at 700 km altitude. The performance of the proposed AGSF is verified using Monte Carlo simulation whose results...
Article IET Radar, Sonar and Navigation ; Volume 10, Issue 7 , 2016 , Pages 1186-1190 ; 17518784 (ISSN) ; Kashani, E. S ; Ajorloo, A ; Sharif University of Technology
Institution of Engineering and Technology 2016
In triangulation (or angle of arrival) target localisation method, the surface of the Earth is approximated by a flat plate. This approximation, while acceptable for low-altitude observers (such as unmanned aerial vehicles), is not a correct model for high-altitude observers (such as low Earth orbit - LEO satellites). In this study, the authors have discussed triangulation method using a LEO satellite observer over a spherical surface and have shown that, using spherical trigonometry and singular value decomposition (SVD), a straight forward solution can be found for target localisation problem. Also, error bound is discussed and analysed using both SVD as well as simulation. © The...
Orbit estimation using a horizon detector in the presence of uncertain celestial body rotation and geometry, Article Acta Astronautica ; Volume 148 , 2018 , Pages 82-88 ; 00945765 (ISSN) ; Hazrati Azad, M ; Assadian, N ; Sharif University of Technology
Elsevier Ltd 2018
This paper presents an orbit estimation using non-simultaneous horizon detector measurements in the presence of uncertainties in the celestial body rotational velocity and its geometrical characteristics. The celestial body is modeled as a tri-axial ellipsoid with a three-dimensional force field. The non-simultaneous modelling provides the possibility to consider the time gap between horizon measurements. An unscented Kalman filter is used to estimate the spacecraft state variables and the geometric characteristics as well as the rotational velocity vector of the celestial body. A Monte-Carlo simulation is implemented to verify the results. Simulations showed that using non-simultaneous...
M.Sc. Thesis Sharif University of Technology ; Pourtakdoust, Hossein ; Kiani, Maryam
Traditionally, orbital maneuvers are obtained according to mission cost, time and several constraints. This thesis considers the use of covariance as a measure of uncertainties in the design of orbit maneuvers. The ideal solution in the proposed method is the maneuver that obtains the minimum uncertainty at the desired times in presence of the mission constraints. In this thesis two impulsive orbit maneuver schemes, based on shaping method and sequential lambert solutions, are developed and has been analyzed under uncertainties. Moreover, a novel rendezvous design methodology is proposed in order to minimize the covariace trace at the impulse locations, considering several constraints...
M.Sc. Thesis Sharif University of Technology ; Asadian, Nima
In this thesis, the orbit determination of Low Earth Orbits (LEO) using the integrated magnetometer and horizon sensor data has been investigated. Orbit determination is an essential part of a space mission. Not only the modeling, guidance, navigation and control errors may results in error in injecting the satellite into its nominal orbit, the environmental disturbances deviate the satellite from its predicted orbit and from an operational perspective most satellites need continuous orbit determination. Traditionally, ground based orbit determination is used which are non-autonomous and expensive and just can be used for specific times which the satellite can be observed from the ground...
Article Acta Astronautica ; Volume 106 , January–February , 2015 , Pages 13-23 ; 00945765 (ISSN) ; Assadian, N ; Sharif University of Technology
Elsevier Ltd 2015
The estimation of the satellite orbital elements using the integrated magnetometer and horizon sensors data has been investigated in this study. These sensors are generally employed for attitude estimation. The magnetometer and the horizon sensor measure the Earths magnetic field as well as the Earths center direction in the body frame, respectively. The magnitude of the magnetic field and the angle between two vectors have been used for orbit estimation purpose. This excludes the knowledge of the attitude in the orbit determination. The Gaussian variation of parameters equations is used for the orbital motion dynamical model to have the orbital elements as the states of the system. Since...
Article RAST 2005 - 2nd International Conference on Recent Advances in Space Technologies, Istanbul, 9 June 2005 through 11 June 2005 ; Volume 2005 , 2005 , Pages 330-334 ; 0780389778 (ISBN); 9780780389779 (ISBN) ; Mehdizadeh, N. S ; Jalali, M. A ; Sharif University of Technology
This research is dedicated to show the possibility of using solar radiation pressure by solar sails for interplanetary flights. In this paper, in addition to the Introduction of solar sailing and physics of solar radiation pressure, the solar sail orbital dynamics for optimal trajectory of an ideal solar sail spacecraft has been studied. It considers the problem of optimal controlling the sail angle so as to execute a minimum-time coplanar orbit transfer from the circular initial orbit to the circular target orbit. The direct collocation optimal control technique is used to transform the state equations to a set of nonlinear algebraic constraint equations. The results of state and control...