Design and development of attitude control system (ACS) using COTS based components for small satellites

Shams, N.; Tanveer, Fahad; Ahmad, Salmiah

doi:10.1109/icast.2008.4747677

Cited by 5 publications

(5 citation statements)

References 1 publication

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“…In the PNSS-1 attitude control subsystem design, the major aim was to achieve a system with small dimensions and weight. The available options for the attitude control were permanent magnets, reaction wheels, and magnetic rods [31,32]. Permanent magnets are cheaper, simpler, and lightweight, but they have inadequate pointing accuracy.…”

Section: Attitude Control System (Acs)mentioning

confidence: 99%

Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite

Ali

Khan

et al. 2018

International Journal of Aerospace Engineering

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The Electric Power System (EPS) and attitude control system (ACS) are the essential components of any satellite. EPS and ACS efficiency and compactness are substantial for the proper operation and performance of the satellite’s entire mission life. So, realizing the significance of EPS and ACS subsystems for any satellite, they have been assimilated and developed in modular forms focusing on efficiency and compactness. The EPS is comprised of three modules called the solar panel module (SPM), power conditioning module (PCM), and power distribution module (PDM) while the ACS has an embedded magnetorquer coil. For compactness and miniaturization purposes, the magnetorquer coil is embedded inside the SPM. The components used are commercial off-the-shelf (COTS) components emphasizing on their power efficiency, small dimensions, and weight. Latch-up protection systems have been designed and analyzed for CMOS-based COTS components, in order to make them suitable for space radioactive environment. The main design features are modularity, redundancy, power efficiency, and to avoid single component failure. The modular development of the EPS and ACS helps to reuse them for future missions, and as a result, the overall budget, development, and testing time and cost are reduced. A specific satellite mission can be achieved by reassembling the required subsystems.

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Section: Attitude Control System (Acs)mentioning

confidence: 99%

Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite

Ali

Khan

et al. 2018

International Journal of Aerospace Engineering

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“…Based on this mechanism, the optimal value of K is determined by using state-space in (4) and (5). The control law is defined as in (15):…”

Section: Linear Quadratic Regulator (Lqr)mentioning

confidence: 99%

“…Attitude control systems (ACS) play a fundamental role in satellite operation and in achieving mission goals. The satellite attitude control problem has been studied extensively where a number of possible approaches have been developed through the years [3][4][5][6]. Many approaches have been developed to control the attitude of satellite such as LQR and LQG, linear matrix inequality(LMI), gain scheduling/linear parameter varying [3], adaptive control/model following, variable structure, sliding mode control, fault tolerant control system (FTCS) and model-based predictive control (MPC) [4].…”

Section: Introductionmentioning

confidence: 99%

“…Many approaches have been developed to control the attitude of satellite such as LQR and LQG, linear matrix inequality(LMI), gain scheduling/linear parameter varying [3], adaptive control/model following, variable structure, sliding mode control, fault tolerant control system (FTCS) and model-based predictive control (MPC) [4]. Nowadays, artificial intelligence techniques such as neural networks [5] and fuzzy logic are also used for obtaining better performance of attitude control.…”

Section: Introductionmentioning

confidence: 99%

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Full-and Reduced- Order Compensator for Innosat Attitude Control

2015

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This paper presents a study on the estimator based on Linear Quadratic Regulator (LQR) control scheme for Innovative Satellite (InnoSAT). By using LQR control scheme, the controller and the estimator has been derived for state space form in all three axes to stabilize the system’s performance. This study starts by converting the transfer functions of attitude control into state space form. Then, the step continues by finding the best value of weighting matrices of LQR in order to obtain the best value of controller gain, K. After that, the best value of L is obtained for the estimator gain. The value of K and L is combined in forming full order compensator and in the same time the reduced order compensator is also formed. Lastly, the performance of full order compensator is compared to reduced order compensator. From the simulation, results indicate that both types of estimators have presented good stability and tracking performance. However, reduced order estimator has simpler equation and faster convergence to zero than the full order estimator. This property is very important in developing a satellite attitude control for real-time implementation.

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“…to bring solar panels in line with the sun and the antenna towards the ground station. For attitude control of the CubeSat different systems are available in the market like permanent magnets, reaction wheel, and magnetic rods [3,4]. Each of them has its own pros and cons.…”

Section: Introductionmentioning

confidence: 99%

Design and comparison of embedded air coils for small satellites

Ali¹,

Mukhtar²,

Ullah³

et al. 2018

Turk J Elec Eng & Comp Sci

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Abstract:The paper discusses the comparison of different shapes of embedded air coils for the attitude control of small satellites. Various systems are available in the market for the attitude control of small satellites such as reaction wheels, permanent magnets, magnetic rods, and thrusters. The available systems have large size, heavier weight, and relatively higher power consumption. A miniaturized system with less power consumption and heat dissipation is required that can provide the anticipated torque. This paper focuses on the design and comparison of square and circular air coils embedded in four internal layers (i.e. 2nd, 3rd, 4th, and 5th) of the eight layer CubeSat power management tile

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Design and development of attitude control system (ACS) using COTS based components for small satellites

Cited by 5 publications

References 1 publication

Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite

Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite

Full-and Reduced- Order Compensator for Innosat Attitude Control

Design and comparison of embedded air coils for small satellites

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