DESIGN, MANUFACTURING AND TEST OF A THREE DEGREES-OF-FREEDOM ATTITUDE CONTROL SIMULATOR FOR AN AGILE MICRO- SATELLITE BASED ON SINGLE GIMBAL CONTROL MOMENT GYROS

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AGHALARI A.R.; KALHOR A.; DEHGHAN S.M.M.; CHEHELTANI S.H.

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Paper Information

Journal: Journal of Space Science and Technology Year:2014 | Volume:7 | Issue:3 Page(s): 51-67

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Title

DESIGN, MANUFACTURING AND TEST OF A THREE DEGREES-OF-FREEDOM ATTITUDE CONTROL SIMULATOR FOR AN AGILE MICRO- SATELLITE BASED ON SINGLE GIMBAL CONTROL MOMENT GYROS

Author(s)

AGHALARI A.R. | KALHOR A. | DEHGHAN S.M.M. | CHEHELTANI S.H. | Issue Writer Certificate

Keywords

SIMULATORQ2

AGILE SATELLITEQ2

ATTITUDE CONTROLQ2

SINGLEQ2

GIMBAL CONTROL MOMENT GYROQ2

AIR BEARINGQ2

Abstract

The AGILE SATELLITE ATTITUDE CONTROL System SIMULATOR (ASACSS) is a laboratory system designed for the purpose of developing and testing ATTITUDE CONTROL algorithms in a low- risk, low- cost environment. In this paper, the design and development of the ASACSS is described, including hardware and software. There are many papers that present a new mathematical technique or prove a new theory, but this study presents the design and development of a new experimental system. This SIMULATOR consists of four main components: 1) power supply system 2) on-board control system 3) supporting equipments and 4) monitoring computer. On-board control system includes a industrial computer, four SINGLE GIMBAL CONTROL MOMENT GYROs and a sensor for attitude determination. Supporting equipments include a platform for installing SIMULATOR subsystems, a semi-spherical AIR BEARING and a pedestal. A high-speed wireless LAN connection enables remote command initiation, monitoring and data collection for post- experimental analysis. In this paper, The design and construction process of the SIMULATOR are described. More over some experimental results presented from the application of a simple PID ATTITUDE CONTROLler on the spacecraft SIMULATOR. Finally, experimental results are compared with those obtained from simulation.

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APA: Copy

AGHALARI, A.R., KALHOR, A., DEHGHAN, S.M.M., & CHEHELTANI, S.H.. (2014). DESIGN, MANUFACTURING AND TEST OF A THREE DEGREES-OF-FREEDOM ATTITUDE CONTROL SIMULATOR FOR AN AGILE MICRO- SATELLITE BASED ON SINGLE GIMBAL CONTROL MOMENT GYROS. JOURNAL OF SPACE SCIENCE AND TECHNOLOGY (JSST), 7(3 ), 51-67. SID. https://sid.ir/paper/149993/en

Vancouver: Copy

AGHALARI A.R., KALHOR A., DEHGHAN S.M.M., CHEHELTANI S.H.. DESIGN, MANUFACTURING AND TEST OF A THREE DEGREES-OF-FREEDOM ATTITUDE CONTROL SIMULATOR FOR AN AGILE MICRO- SATELLITE BASED ON SINGLE GIMBAL CONTROL MOMENT GYROS. JOURNAL OF SPACE SCIENCE AND TECHNOLOGY (JSST)[Internet]. 2014;7(3 ):51-67. Available from: https://sid.ir/paper/149993/en

IEEE: Copy

A.R. AGHALARI, A. KALHOR, S.M.M. DEHGHAN, and S.H. CHEHELTANI, “DESIGN, MANUFACTURING AND TEST OF A THREE DEGREES-OF-FREEDOM ATTITUDE CONTROL SIMULATOR FOR AN AGILE MICRO- SATELLITE BASED ON SINGLE GIMBAL CONTROL MOMENT GYROS,” JOURNAL OF SPACE SCIENCE AND TECHNOLOGY (JSST), vol. 7, no. 3 , pp. 51–67, 2014, [Online]. Available: https://sid.ir/paper/149993/en

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