Correction: CubeSat Attitude Control Simulator Design

PLUG AND PLAY INNOSAT ACS SIMULATOR

Jurnal Teknologi ◽

10.11113/jt.v76.5617 ◽

2015 ◽

Vol 76 (8) ◽

Author(s):

S. M. Sharun ◽

M. Y. Mashor ◽

Fadzilah Hashim

Keyword(s):

Attitude Control ◽

Operating Conditions ◽

Matlab Simulation ◽

Dynamics Model ◽

Attitude Control System ◽

Close Match ◽

Novel Approach ◽

Simulator Design ◽

Hardware In Loop ◽

Hardware In Loop Simulation

This research proposes a novel approach of satellite simulator design where the simulator will be in the form of both software and hardware. A software simulator will represent the satellite dynamics model, incorporating all the operating conditions of the satellite in orbit. The control algorithm for Attitude Control System (ACS) will be implemented on Rabbit Micro Controller (RCM4100) and the dynamics model of Innovative Satellite (InnoSAT) plant in PC have been tested using real-time hardware-in-loop-simulation (HILS) technique. The results that have been obtained show that the InnoSAT ACS simulator can produce as good result as MATLAB simulation for the InnoSAT plants. The MSE values that have been calculated also show that there are a close match between HILS and MATLAB simulation where the MSEs different value are small. From both results, it is enough to verify that the developed protocol working satisfyingly and seems to be possible to be implemented on the actual flight.

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A Systems Engineering Tool for Satellite Simulator Design

ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis, Volume 5 ◽

10.1115/esda2010-25341 ◽

2010 ◽

Cited By ~ 2

Author(s):

Mehran Mirshams ◽

M. Amin Vahid D. ◽

Hojjat Taei

Keyword(s):

Systems Engineering ◽

Attitude Control ◽

Degrees Of Freedom ◽

System Engineering ◽

Iterative Solvers ◽

Space Research ◽

Dynamics Simulation ◽

Satellite Attitude ◽

Operational Tests ◽

Simulator Design

Simulation is one of the best methods for education and understanding events and used in many fields of science, for example: space researches. For this reason, creating of a frictionless environment that can simulate the operations of satellites will be very usable and appropriate. Spherical air bearings, that we call them TESTBEDs in this paper, are one of the most common devices used in satellite attitude dynamics simulation, because they provide three degrees of freedom rotational motion. They are employed to develop, improve and carry out operational tests of sensors, actuators and attitude control algorithms in experimental framework. An explanation about system engineering tool for testbed design that used by our team in Space Research Lab will be presented in this paper. This systems engineering tool utilizes a testbed-based approach to efficiently track information regarding the mass, cost, operation and volume of simulator subsystems. This subsystem information is derived through a variety of means, including analytical relationships, iterative solvers, and databases of components appropriate for satellite simulators. Finally, a description of 3-DoF satellite simulator and it’s subsystems (manufactured in Space Research Lab) by means of this system engineering tool will be demonstrated as a sample for validating results.

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Design and Validation of the University of Naples Space Magnetic Field Simulator (SMAFIS)

Journal of the IEST ◽

10.17764/jiet.44.1.y2401q13726534t7 ◽

2001 ◽

Vol 44 (1) ◽

pp. 33-42 ◽

Cited By ~ 1

Author(s):

M. Pastena ◽

L. Sorrentino ◽

M. Grassi

Keyword(s):

Magnetic Field ◽

Attitude Control ◽

Field Vector ◽

Open Loop ◽

Magnetic Field Vector ◽

Local Magnetic Field ◽

Test Volume ◽

Magnetic Attitude Control ◽

Simulator Design ◽

The University

This paper discusses the design and validation of the space magnetic field simulator at the university of Naples. The simulator is designed to reproduce, with predetermined uniformity, the magnetic field vector as sensed by an orbiting satellite in the an assigned volume about the simulator's geometrical center. The simulator will be used primarily for ground testing the magnetic attitude control subsystem onboard the university microsatellite SMART. The paper describes the criteria as well as the mathematical model used for the simulator design. The design aims mainly at developing a simulator configuration that maximizes the volume in which the desired magnetic field vector is realized with a predetermined uniformity with respect to a nominal field. The simulator is configured as an open-loop system, in which fixed currents are used to nullify the local magnetic field. Precision currents are then added to the fixed ones to accurately reproduce, in the test volume, the in-orbit magnetic field vector variation. Results of the simulator validation tests are presented.

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