عرفان شكورزاده

In this thesis, Relative position control of Satellite constellation using the atmospheric drag method in the long term based on ground station software (GS in Loop) designed to create desired configurations in the satellite constellation whose satellites are moving in circular orbits, while executing the control commands and creating different configurations for satellite constellation is a simple and cheap subsystem. In this regard, Hill Clohesi Wiltshire's dynamics has been used to investigate the relative behavior of satellites. by using the two capabilities of detecting the entry into the earth's shadow and the ability to communicate a satellite with its neighbor satellite, to design and implement the backward forward control law using Atmospheric drag force to control the relative position of satellites to create a desired configuration in the satellite constellation. At first, the definitions related to coordinate systems, distributed space systems, satellite constellations and relative position control for satellites presented, then the equations related to the atmospheric drag force extracted to use as a control force and control force added to it, then The effects of land heterogeneity have been included in these equations and new equations extracted. By providing a simple method to determine the relative position of satellites using a simple photodiode sensor, the control law defined and the equations related to the relative position error extracted then ground station software that complies with the European unio‎n Space Agency Designed and implemented to display real-time position of satellites to user and send telecommands to satellites. In the following, the position control system using atmospheric drag has been implemented in such way that meeting control goals, while complexity in the control rules avoided. for satellite constellation consist 8 satellites located in a circular orbit in the same plane, Position of each satellite, relative position of each satellite in relation to its leading satellite, the speed of each satellite and relative speed of each satellite to its leading satellite, the true anomaly of each satellite and the relative anomaly of each satellite with its leading satellite, The desired relative position error with respect to the current position for each satellite and its leading satellite and the control force at each moment, has been simulated and investigated. At the end of each sections, the correctness of the design shown by performing simulation.

منظومه ماهواره‌اي , كنترل پيشرو پسرو , معادلات هيل كلوهسي ويلتشاير , كشش اتمسفري , كنترل موقعيت نسبي

atmospheric drag , forward backward control , clohesi wiltshire equations , relative position control , satellite constellation

Erfan shakourzadeh

dr. bahman ghorbani vaghei