Active control for initial attitude acquisition using magnetic torquers

Jan, Y.W.; Tsai, Jih-Run

doi:10.1016/j.actaastro.2005.03.067

Cited by 15 publications

(10 citation statements)

References 1 publication

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“…The weight , and and threshold, are unknowns and should be selected to minimize the prediction error, define as: (6) where is the desire output and is the actual output. …”

Section: A Hybrid Multi Layered Perceptron Networkmentioning

confidence: 99%

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Adaptive Neuro-controller based on HMLP network for InnoSAT attitude control

Sharun

Mashor

Norhayati

et al. 2011

International Conference on Electrical, Control and Computer Engineering 2011 (InECCE)

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In this paper, an intelligence controller namely Adaptive Neuro-controller (ANC) based on Hybrid Multilayered Perceptron (HMLP) network is developed for the attitude control of a nano-satellite. The objective of this paper is to compare the tracking performance between ANC based on HMLP network and ANC based on standard MLP network for controlling a satellite attitude. Both ANC's use Model Reference Adaptive Control (MRAC) as a control scheme. The control scheme was used to control a time varying systems where the performance specifications are given in terms of a reference model. Weighted Recursive Least Square (WRLS) algorithm has been used to adjust the controller parameters to minimize the error between the actual output and the reference input. Y-Thompson spin control is adapted to the satellite system as the reference input throughout the simulation. These controllers have been tested using Innovative Satellite (InnoSAT) plant with some variations in operating conditions such as varying gain, noise and disturbance. The simulation results indicated that ANC based on HMLP network is adequate to control satellite attitude and gave better result than the ANC based on MLP network.

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“…The weight , and and threshold, are unknowns and should be selected to minimize the prediction error, define as: (6) where is the desire output and is the actual output. …”

Section: A Hybrid Multi Layered Perceptron Networkmentioning

confidence: 99%

“…The ACS system should be a low-cost controller as well as a high reliability which can be applied and embedded to a real time application. [5][6].…”

Section: Introductionmentioning

confidence: 98%

Adaptive Neuro-controller based on HMLP network for InnoSAT attitude control

Sharun

Mashor

Norhayati

et al. 2011

International Conference on Electrical, Control and Computer Engineering 2011 (InECCE)

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“…In this part, test result of implementing attitude control algorithms in HIL test bed is presented, where attitude determination results are extracted from simulator model. Here, detumbling and initial attitude acquisition control modes are implemented in OBE and obtained result will be compared with result of simulations based on references [14,15]. In detumbling mode the mission is to reduce tumbling of satellite, originated from injection of satellite in orbit by launcher [16] and in initial attitude acquisition mode the mission is to orienting satellite Z axis toward the earth magnetic field vector [15].…”

Section: Implementing Attitude Control Algorithms In Hil Test Bedmentioning

confidence: 99%

“…Proof of detumbling is presented in [14]. Also based on [15], a useful control law for initial attitude acquisition is as follow:…”

Section: Implementing Attitude Control Algorithms In Hil Test Bedmentioning

confidence: 99%

Satellite Attitude Determination and Contol

Bolandi

Haghparast

Saberi

et al. 2012

Measurement and Control

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Attitude Determination and Control Subsystem (ADCS) is one of the vital subsystem of satellites which has a significant role in performing satellites missions. On-Board Electronic (OBE) is the main part of this subsystem which executes attitude determination and control algorithms. In this paper design of OBE of ADCS in IUST-SAT is presented. Design of this equipment is carried out based on requirements and constraints which are extracted by hierarchical design procedure. Satisfying design constraints and achieving functional requirements simultaneously, is a major task, which is carried out successfully in this paper. Also for verification of performance of this equipment before a satellite's launch, in this paper a novel and low-cost real-time hardware in the loop test bed is provided. The presented test bed is capable of assessing ADCS's equipments in a real-time condition. Finally, performance of designed OBE is investigated by implementing detumbling and initial attitude acquisition control modes in the hardware in the loop test bed.

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“…A linear time-varying (LTV) approach to control satellite attitude was developed by using only magnetorquers 25 . Initial attitude acquisition was demonstrated using magnetorquers 26 . In addition, time-optimal control 27 , neural network control 28 , and H ∞ control 29 techniques were also used along with some other work [30][31][32] in controlling spacecraft attitude using only magnetorquers.…”

Section: Introductionmentioning

confidence: 99%

Magnetorquers only Attitude Maintaining Using Dynamic Attitude Simulator Environment

Gulmammadov

Kahraman

Yavuzyilmaz

et al. 2010

AIAA Modeling and Simulation Technologies Conference

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Magnetic controllers for maintaining and varying spacecraft's directivity using only magnetorquers are presented using dynamic attitude simulator environment (DASE), which includes a flight computer and the complete satellite communications architecture. Magnetorquers are environmental actuators that on the contrary to reaction wheels do not have any moving parts. For that reason using only magnetorquers for the tasks where precise attitude control is not required prolongs mission lifetime. Despite the inability to produce torque along the Earth's magnetic field vector magnetorquers can still provide the sufficient pointing accuracy for the on-board antennae with help of B-max and VBC controllers. The controllers are designed for RASAT, an Earth observation satellite, to be launched to a sun-synchronous low Earth orbit (LEO) orbit. The satellite ground communication is achieved via rigidly mounted X-band and S-band antennae with restricted radiation patterns. The controllers' purpose is to maximize the high speed communication duration by directing the satellite's side where the antennae are located towards the ground station during each pass. The results show that magnetic actuation provides sufficient pointing accuracy that surpasses the Nadir-pointing flight mode in terms of communication duration. Nomenclature e = error received by a controller SET v = set-point vector B = Earth' magnetic field vector as measured in satellite's body frame m = magnetic dipole moment vector expressed in satellite's body frame  τ = torque vector Z = satellite's +Z vector expressed in orbit frame P K = proportional gain of a controller D K = differential gain of a controller b o R = rotation matrix from orbit frame to body frame / b bi ω  = angular velocity vector of satellite body frame with respect to inertial frame, represented in satellite body frame. I = Inertia matrix of the satellite D T  = total disturbance torques MT T  = torques generated by the magnetorquers 1 Researcher, Electrical and Electronics Engineer, M.Sc.

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Active control for initial attitude acquisition using magnetic torquers

Cited by 15 publications

References 1 publication

Adaptive Neuro-controller based on HMLP network for InnoSAT attitude control

Adaptive Neuro-controller based on HMLP network for InnoSAT attitude control

Satellite Attitude Determination and Contol

Magnetorquers only Attitude Maintaining Using Dynamic Attitude Simulator Environment

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