In this paper, nonlinear attitude model of a satellite with pyramid Control Moment Gyros (CMG) and other with pyramid Fluid Momentum Controller (FMC) is developed. A comparative study between pyramidal cluster of FMC and CMG is conducted. This comparison is based on simulation of attitude control system a Nano satellite with two different actuators. For comparison purposes, a sliding mode controller based on modified Rodriguez parameters is considered for attitude control system. The efficiency of maneuvers, agility, power consumption, mass and capability of combination actuators have been compared for two different actuators. Results show that both systems successfully conducted different agile maneuvers and have a good performance in controller against disturbance. In same power consumption, capacity of CMG torque generation is more than FMC actuators.
Purpose The purpose of this paper is to simulate the thermal performance of fluidic momentum controller (FMC) actuators in two case, with and without thermal distribution system on a three-axis configuration of FMC actuators to an orbital period of satellite. The results show the effectiveness of using a storage with FMC actuators. Design/methodology/approach One of the challenges during a satellite’s orbital mission is unpredictable external temperature perturbations. This system used as a collaborative thermal subsystem for microsatellite temperature passive control. The operating principles of the system are that each fluid rings are used in a microsatellite surface with pumps to stabilize the satellite. All fluid rings are connected to the satellite thermal distribution system (storage). Findings Simulation results show that with using of thermal distribution system, damping of satellite different surfaces temperature is rapidly possible to the event of thermal disturbances. Practical implications Numerical simulation is obtained by ANSYS Fluent software and pressure-velocity coupling is SIMPLE method and spatial discretization is second order accurate and first order in time, viscous model is k-e. In this regard, a solver algorithm is also developed. Originality/value In space research fields about FMC application as actuators to satellite system design, main goal is to research about role of this system to attitude and determination control system (ADCS) of satellites, and no study is performed on its role to satellite temperature damping. This study is exclusively simulated thermal distribution system (includes a storage and its connections) of a microsatellite equipped with FMC actuators. The idea of using a storage for FMC actuators is the innovative step of this research.
Purpose -The purpose of this research was to analyze application effects of the stable frozen orbit conditions in the spacecraft Orbital Maintenance Maneuver (OMM) reduction. Design/methodology/approach -One challenge in implementing these motions is maintaining the relations as it experiences orbital perturbations (zonal harmonics), most notably due to the non-spherical Earth. A natural phenomenon exists called a frozen orbit, for which the orbital elements: argument of perigee () and eccentricity (e) remain virtually fixed over extended periods of time. Findings -Simulation results show that, using stable frozen orbit condition results in considerable propellant saving, decreased OMM, increase of accuracy position errors and thus performance improvement of the spacecraft for orbiter mission is preferable. So, from among three proposed theories, the Brouwer-Hori theory has provided better accuracy and more stable conditions in the frozen orbit. Practical implications -Simulation algorithm has been achieved to solve this problem by extracting and combining the equations that govern the frozen conditions with the tangential forces (⌬V) equations for orbit correction. Originality/value -In all studies with content of harmonic perturbation effects on the spacecraft motion dynamics, main goal is to obtain a solution for optimization of the operation process, so that overshadowed mission costs. The case studies about this aim, mostly to the trajectory parameters optimization by considering the vehicle orbital conditions under various control methods are formed. While in this regards, the intrinsic properties of stable Earth orbits and using them effectively is less than to analyse the problems is considered.
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