Hardware-in-the-loop real-time validation of micro-satellite attitude control

• Published in: Computers & electrical engineering Vol. 85; pp. 106679 - 13
• Main Authors: Gaber, Khaled, El_Mashade, Mohamed B., Aziz, Ghada A. Abdel
• Format: Journal Article
• Language: English
• Published: Amsterdam Elsevier Ltd 01.07.2020; Elsevier BV
• Subjects: Attitude control; Attitude determination; Control systems design; Controllers; Design parameters; Drift; Hardware-in-the-loop; Hardware-in-the-loop simulation; MEMS gyro; Micro-satellite; Microsatellites; Model accuracy; Proportional integral; Real time; Satellite attitude control; Satellite tracking; Satellites; Small satellites; Spacecraft; Micro-satellite; Attitude control; Attitude determination; Hardware-in-the-loop; MEMS gyro
• ISSN: 0045-7906; 1879-0755
• DOI: 10.1016/j.compeleceng.2020.106679

•This paper presents the design of modified proportional-integral attitude controller approach for adjusting the microsatellite's attitude without the need for parameters gains.•The presented microsatellite's attitude determination and control system is experimentally implemented via hardware-in-the-loop platform.•The hardware-in-the-loop eliminates the high costs of using real hardware in the attitude control of satellite systems.•The attitude determination and control system emulated model has accuracy results with attitude error of less than 0.01 degree. This paper presents the real-time validation of micro-satellite (MS) attitude determination and control system (ADCS) using modified proportional-integral (MPI) attitude control on the hardware-in-the-loop (HIL) platform. This platform eliminates the high costs of using real hardware in attitude control of satellite system and enables researchers to develop new, rapid, and reliable controllers in space tests. Due to the increasing demands for using small satellites in space, MS requires accurate ADCS and attitude drift regulation. In case the non-proper compensation of the attitude drift, thus, attitude information will be lost as the attitude error will be rise between actual along with estimated signals. MS's attitude is determined by estimating its current attitude and the attitude control is performed via using MPI attitude controller which can precisely correct the MS's attitude. This controller has simple design without controller gains parameters. ADCS emulated model has accuracy results with attitude error approximately 0.01 degree. [Display omitted]