This page has only limited features, please log in for full access.

Unclaimed
N. M. Suhadis
School of Aerospace Engineering, Engineering Campus, Universiti Sains Malaysia, Nibong Tebal 14300, Pulau Pinang, Malaysia

Honors and Awards

The user has no records in this section


Career Timeline

The user has no records in this section.


Short Biography

Ir. Dr. Nurulasikin Mohd Suhadis is currently an academic in the School of Aerospace Engineering at Universiti Sains Malaysia. She completed he Ph.D in Aerospace Engineering from Universiti Putra Malaysia, Malaysia in 2007. Her research includes Satellite & Flight Controls.

Following
Followers
Co Authors
The list of users this user is following is empty.
Following: 0 users

Feed

Journal article
Published: 27 April 2021 in Aerospace
Reads 0
Downloads 0

This paper presents an optimization algorithm named Random Explosion Algorithm (REA). The fundamental idea of this algorithm is based on a simple concept of the explosion of an object. This object is commonly known as a particle: when exploded, it will randomly disperse fragments around the particle within the explosion radius. The fragment that will be considered as a search agent will fill the local space and search that particular region for the best fitness solution. The proposed algorithm was tested on 23 benchmark test functions, and the results are validated by a comparative study with eight well-known algorithms, which are Particle Swarm Optimization (PSO), Artificial Bee Colony (ABC), Genetic Algorithm (GA), Differential Evolution (DE), Multi-Verse Optimizer (MVO), Moth Flame Optimizer (MFO), Firefly Algorithm (FA), and Sooty Tern Optimization Algorithm (STOA). After that, the algorithm was implemented and analyzed for a quadrotor control application. Similarly, a comparative study with the other algorithms stated was done. The findings reveal that the REA can yield very competitive results. It also shows that the convergence analysis has proved that the REA can converge more quickly toward the global optimum than the other metaheuristic algorithms. For the control application result, the REA controller can better track the desired reference input with shorter rise time and settling time, lower percentage overshoot, and minimal steady-state error and root mean square error (RMSE).

ACS Style

Mohamad Shauqee; Parvathy Rajendran; Nurulasikin Suhadis. An Explosion Based Algorithm to Solve the Optimization Problem in Quadcopter Control. Aerospace 2021, 8, 125 .

AMA Style

Mohamad Shauqee, Parvathy Rajendran, Nurulasikin Suhadis. An Explosion Based Algorithm to Solve the Optimization Problem in Quadcopter Control. Aerospace. 2021; 8 (5):125.

Chicago/Turabian Style

Mohamad Shauqee; Parvathy Rajendran; Nurulasikin Suhadis. 2021. "An Explosion Based Algorithm to Solve the Optimization Problem in Quadcopter Control." Aerospace 8, no. 5: 125.

Journal article
Published: 17 March 2021 in Applied Sciences
Reads 0
Downloads 0

A hybrid proportional double derivative and linear quadratic regulator (PD2-LQR) controller is designed for altitude (z) and attitude (roll, pitch, and yaw) control of a quadrotor vehicle. The derivation of a mathematical model of the quadrotor is formulated based on the Newton–Euler approach. An appropriate controller’s parameter must be obtained to obtain a superior control performance. Therefore, we exploit the advantages of the nature-inspired optimization algorithm called Grey Wolf Optimizer (GWO) to search for those optimal values. Hence, an improved version of GWO called IGWO is proposed and used instead of the original one. A comparative study with the conventional controllers, namely proportional derivative (PD), proportional integral derivative (PID), linear quadratic regulator (LQR), proportional linear quadratic regulator (P-LQR), proportional derivative and linear quadratic regulator (PD-LQR), PD2-LQR, and original GWO-based PD2-LQR, was undertaken to show the effectiveness of the proposed approach. An investigation of 20 different quadcopter models using the proposed hybrid controller is presented. Simulation results prove that the IGWO-based PD2-LQR controller can better track the desired reference input with shorter rise time and settling time, lower percentage overshoot, and minimal steady-state error and root mean square error (RMSE).

ACS Style

Mohamad Shauqee; Parvathy Rajendran; Nurulasikin Suhadis. Proportional Double Derivative Linear Quadratic Regulator Controller Using Improvised Grey Wolf Optimization Technique to Control Quadcopter. Applied Sciences 2021, 11, 2699 .

AMA Style

Mohamad Shauqee, Parvathy Rajendran, Nurulasikin Suhadis. Proportional Double Derivative Linear Quadratic Regulator Controller Using Improvised Grey Wolf Optimization Technique to Control Quadcopter. Applied Sciences. 2021; 11 (6):2699.

Chicago/Turabian Style

Mohamad Shauqee; Parvathy Rajendran; Nurulasikin Suhadis. 2021. "Proportional Double Derivative Linear Quadratic Regulator Controller Using Improvised Grey Wolf Optimization Technique to Control Quadcopter." Applied Sciences 11, no. 6: 2699.

Conference paper
Published: 13 June 2020 in Lecture Notes in Mechanical Engineering
Reads 0
Downloads 0

The number of CubeSats launched since the first group of six CubeSats was launched in March 2003 has increased. Several reliable databases that collect CubeSat information show that 1035 CubeSats have been launched as of 31 December, 2018. The author has taken the opportunity to use the information published in these databases and presents a statistical overview of CubeSat missions in this paper. This overview will hopefully be beneficial to the readers.

ACS Style

N. M. Suhadis. Statistical Overview of CubeSat Mission. Lecture Notes in Mechanical Engineering 2020, 563 -573.

AMA Style

N. M. Suhadis. Statistical Overview of CubeSat Mission. Lecture Notes in Mechanical Engineering. 2020; ():563-573.

Chicago/Turabian Style

N. M. Suhadis. 2020. "Statistical Overview of CubeSat Mission." Lecture Notes in Mechanical Engineering , no. : 563-573.

Conference paper
Published: 01 May 2018 in IOP Conference Series: Materials Science and Engineering
Reads 0
Downloads 0
ACS Style

N M Suhadis; M B Salleh; P Rajendran. Magnetic attitude control torque generation of a gravity gradient stabilized satellite. IOP Conference Series: Materials Science and Engineering 2018, 370, 1 .

AMA Style

N M Suhadis, M B Salleh, P Rajendran. Magnetic attitude control torque generation of a gravity gradient stabilized satellite. IOP Conference Series: Materials Science and Engineering. 2018; 370 ():1.

Chicago/Turabian Style

N M Suhadis; M B Salleh; P Rajendran. 2018. "Magnetic attitude control torque generation of a gravity gradient stabilized satellite." IOP Conference Series: Materials Science and Engineering 370, no. : 1.

Conference paper
Published: 01 May 2018 in IOP Conference Series: Materials Science and Engineering
Reads 0
Downloads 0

In this paper, the gimbal angle compensation method using magnetic control law has been adopted for a small satellite operating in low earth orbit under disturbance toques influence. Three light weight magnetic torquers have been used to generate the magnetic compensation torque to bring diverge gimbals at preferable angle. The magnetic control torque required to compensate the gimbal angle is based on the gimbal error rate which depends on the gimbal angle converging time. A simulation study has been performed without and with the MTGAC system to investigate the amount of generated control torque as a trade-off between the power consumption, attitude control performance and CMG dynamic performance. Numerical simulations show that the satellite with the MTGAC system generates more control torques which leads to the additional power requirement but in return results in a favorable attitude control performance and gimbal angle management.

ACS Style

M B Salleh; N M Suhadis; P Rajendran; N M Mazlan. Control torque generation of a CMG-based small satellite with MTGAC system: a trade-off study. IOP Conference Series: Materials Science and Engineering 2018, 370, 012045 .

AMA Style

M B Salleh, N M Suhadis, P Rajendran, N M Mazlan. Control torque generation of a CMG-based small satellite with MTGAC system: a trade-off study. IOP Conference Series: Materials Science and Engineering. 2018; 370 (1):012045.

Chicago/Turabian Style

M B Salleh; N M Suhadis; P Rajendran; N M Mazlan. 2018. "Control torque generation of a CMG-based small satellite with MTGAC system: a trade-off study." IOP Conference Series: Materials Science and Engineering 370, no. 1: 012045.

Conference paper
Published: 13 May 2016 in SpaceOps 2016 Conference
Reads 0
Downloads 0
ACS Style

Mohd Badrul Salleh; Nurulasikin Mohd Suhadis. Roll Attitude Maneuver of CMG-Based Controlled Small Satellite with Magnetic Torque Gimbal Angle Compensation System. SpaceOps 2016 Conference 2016, 1 .

AMA Style

Mohd Badrul Salleh, Nurulasikin Mohd Suhadis. Roll Attitude Maneuver of CMG-Based Controlled Small Satellite with Magnetic Torque Gimbal Angle Compensation System. SpaceOps 2016 Conference. 2016; ():1.

Chicago/Turabian Style

Mohd Badrul Salleh; Nurulasikin Mohd Suhadis. 2016. "Roll Attitude Maneuver of CMG-Based Controlled Small Satellite with Magnetic Torque Gimbal Angle Compensation System." SpaceOps 2016 Conference , no. : 1.

Journal article
Published: 30 April 2015 in International Review of Aerospace Engineering (IREASE)
Reads 0
Downloads 0

This paper extends the results of the previous work published by the same Authors. It focused on the performance of the Magnetic Torque Gimbal Angle Compensation (MTGAC) system. While the incorporation of the MTGAC system compensated the drifted gimbals angle favorably, the attitude performance of the satellite is also expected to be affected. Therefore, evaluation through numerical simulations using Matlab®/Simulink® software to see the effect of the MTGAC on the satellite attitude performance is performed where the attitude performance of the configured satellite during gimbal angle compensation for both with and without MTGAC system are generated and compared. Results from the simulation exhibit that the satellite attitude performance is improved with incorporation of MTGAC system. Copyright © 2015 Praise Worthy Prize - All rights reserved.

ACS Style

Mohd Badrul Salleh; Nurulasikin Mohd Suhadis. Satellite Attitude Performance of CMG-Based Controlled Small Satellite During Gimbal Angle Compensation. International Review of Aerospace Engineering (IREASE) 2015, 8, 81 .

AMA Style

Mohd Badrul Salleh, Nurulasikin Mohd Suhadis. Satellite Attitude Performance of CMG-Based Controlled Small Satellite During Gimbal Angle Compensation. International Review of Aerospace Engineering (IREASE). 2015; 8 (2):81.

Chicago/Turabian Style

Mohd Badrul Salleh; Nurulasikin Mohd Suhadis. 2015. "Satellite Attitude Performance of CMG-Based Controlled Small Satellite During Gimbal Angle Compensation." International Review of Aerospace Engineering (IREASE) 8, no. 2: 81.

Journal article
Published: 28 February 2015 in International Review of Aerospace Engineering (IREASE)
Reads 0
Downloads 0

The presence of external disturbance torques causes the gimbals angle of Control Moment Gyros (CMG) used to control satellite drift from their preferred initial value. This scenario will drive the CMG into singular states or result in attitude error thus reducing the chance to do slew maneuver. In this paper, a novel method to compensate drifted gimbals of CMG based controlled small satellite operated in low earth orbit is adopted. The satellite is equipped with four Single Gimbal CMG (SGCMG) pyramid-array configuration. Three magnetic torquers are used to generate the compensation control torque where the controlleris designed based on the gimbal angle converging time. Simulations are performed using Matlab®/Simulink® software for various value of gimbals angle converging time to optimize the compensator performance. Results from simulation show that the optimal performance of the system is when the converging time is set at100s. Copyright © 2015 Praise Worthy Prize - All rights reserved.

ACS Style

Mohd Badrul Salleh; Nurulasikin Mohd Suhadis. Magnetic Gimbal Angle Compensator of CMG-Based Controlled Small Satellite. International Review of Aerospace Engineering (IREASE) 2015, 8, 10-15 .

AMA Style

Mohd Badrul Salleh, Nurulasikin Mohd Suhadis. Magnetic Gimbal Angle Compensator of CMG-Based Controlled Small Satellite. International Review of Aerospace Engineering (IREASE). 2015; 8 (1):10-15.

Chicago/Turabian Style

Mohd Badrul Salleh; Nurulasikin Mohd Suhadis. 2015. "Magnetic Gimbal Angle Compensator of CMG-Based Controlled Small Satellite." International Review of Aerospace Engineering (IREASE) 8, no. 1: 10-15.

Journal article
Published: 01 October 2014 in Applied Mechanics and Materials
Reads 0
Downloads 0

In this paper, a three-axis attitude control of a small satellite employing control moment gyroscope (CMG) is presented. A four single gimbal control moment gyroscopes (4-SGCMG) cluster has been employed as the actuator and a proportional-derivative (PD) based attitude control approach has been utilized. The singularity robust (SR) steering law has been employed to investigate its capability in avoiding the singularity state of the CMG system with respect to the mission operation by setting the initial gimbal angle further from the singularity state. The presented control law was simulated in the MATLAB® SIMULINK® software. Results obtained from the simulation show the effectiveness of the control algorithm.

ACS Style

Mohd Badrul Salleh; Nurulasikin Mohd Suhadis. Three-Axis Attitude Control Performance of a Small Satellite Using Control Moment Gyroscope. Applied Mechanics and Materials 2014, 629, 286 -290.

AMA Style

Mohd Badrul Salleh, Nurulasikin Mohd Suhadis. Three-Axis Attitude Control Performance of a Small Satellite Using Control Moment Gyroscope. Applied Mechanics and Materials. 2014; 629 ():286-290.

Chicago/Turabian Style

Mohd Badrul Salleh; Nurulasikin Mohd Suhadis. 2014. "Three-Axis Attitude Control Performance of a Small Satellite Using Control Moment Gyroscope." Applied Mechanics and Materials 629, no. : 286-290.

Journal article
Published: 01 June 2014 in The International Journal of Multiphysics
Reads 0
Downloads 0

This paper describes a comparison study of magnetic attitude control torque generation performance of a momentum bias satellite operated in Low Earth Orbit (LEO) with various orbit inclinations. The satellite is equipped with two magnetic torquers that are placed along the +x and +y axes where magnetic control torque is generated when these magnetic torquers couple with the geomagnetic fields and its vector direction is perpendicular to both the magnetic fields. The control algorithm was structured using a proportional (P) controller for satellite attitudes/nutation control and a proportional-integral (PI) controller for managing the excess angular momentum on the momentum wheel. The structured control algorithm is simulated for 23°, 53° and 83° orbit inclinations and the generated attitude torque performances are compared to see how the variation of the satellite orbit affects the satellite's attitude torque generation as the magnitude and direction of the geomagnetic fields vary with respect to the altitude and latitude while the magnitude and direction of the magnetic fields generated by the magnetic torquers vary with respect to the orbital motion. Results from simulation show that the higher orbit inclination generates optimum magnetic attitude control torque. Note that this work is the extension of the previous work published in The International Journal of Multiphysics [1]

ACS Style

Nurulasikin Mohd Suhadis; Renuganth Varatharajoo. An optimum magnetic control torque generation of a momentum bias satellite. The International Journal of Multiphysics 2014, 8, 169 -180.

AMA Style

Nurulasikin Mohd Suhadis, Renuganth Varatharajoo. An optimum magnetic control torque generation of a momentum bias satellite. The International Journal of Multiphysics. 2014; 8 (2):169-180.

Chicago/Turabian Style

Nurulasikin Mohd Suhadis; Renuganth Varatharajoo. 2014. "An optimum magnetic control torque generation of a momentum bias satellite." The International Journal of Multiphysics 8, no. 2: 169-180.

Journal article
Published: 01 December 2013 in Applied Mechanics and Materials
Reads 0
Downloads 0

This paper presents the experimental determination of the moment of inertia of USM e-UAV by using pendulum method. Compound pendulum experiment is used to determine the moment of inertia about x and y axes while the moment of inertia about z-axis is determined using bifilar torsion pendulum method. An experimental setup is developed with appropriate dimension to accommodate USM e-UAV. Experimental data are presented and discussed.

ACS Style

M. Haniff Junos; Nurulasikin Mohd Suhadis; Mahmud M. Zihad. Experimental Determination of the Moment of Inertias of USM e-UAV. Applied Mechanics and Materials 2013, 465-466, 368 -372.

AMA Style

M. Haniff Junos, Nurulasikin Mohd Suhadis, Mahmud M. Zihad. Experimental Determination of the Moment of Inertias of USM e-UAV. Applied Mechanics and Materials. 2013; 465-466 ():368-372.

Chicago/Turabian Style

M. Haniff Junos; Nurulasikin Mohd Suhadis; Mahmud M. Zihad. 2013. "Experimental Determination of the Moment of Inertias of USM e-UAV." Applied Mechanics and Materials 465-466, no. : 368-372.

Journal article
Published: 01 November 2012 in Applied Mechanics and Materials
Reads 0
Downloads 0

In this paper, the Proportional-Derivative (PD) based attitude control algorithm of the gravity gradient stabilized satellite has been developed. The satellite is equipped with 3 magnetic torquers where each of the magnetic torquer is placed along the +x, +y, +z axes. The control torque is generated when the magnetic field generated by the magnetic torquers couples with the geomagnetic fields, whereby the vector of the generated torque is perpendicular to both the magnetic fields. The developed control algorithm was simulated using the complex and simplified geomagnetic field models for a Low Earth Orbit (LEO) satellite mission in a nominal attitude operation. Results from simulations exhibit the effectiveness of the attitude control torque generation that fulfills the mission attitude control requirements.

ACS Style

Nurulasikin Mohd Suhadis; Renuganth Varatharajoo; Varatharajoo Renuganth. Passive Attitude Control Torque Generation Performances of a Gravity Gradient Stabilized Satellite. Applied Mechanics and Materials 2012, 225, 458 -463.

AMA Style

Nurulasikin Mohd Suhadis, Renuganth Varatharajoo, Varatharajoo Renuganth. Passive Attitude Control Torque Generation Performances of a Gravity Gradient Stabilized Satellite. Applied Mechanics and Materials. 2012; 225 ():458-463.

Chicago/Turabian Style

Nurulasikin Mohd Suhadis; Renuganth Varatharajoo; Varatharajoo Renuganth. 2012. "Passive Attitude Control Torque Generation Performances of a Gravity Gradient Stabilized Satellite." Applied Mechanics and Materials 225, no. : 458-463.

Journal article
Published: 01 March 2012 in The International Journal of Multiphysics
Reads 0
Downloads 0

Magnetic torquers are specifically designed to generate a magnetic field onboard the satellites for their attitude control. A control torque is generated when the magnetic fields generated by the magnetic torquers couple with the geomagnetic fields, whereby the vector of the generated torque is perpendicular to both the magnetic fields. In this paper, two control algorithms for a momentum bias satellite implementing two and three magnetic torquers onboard have been developed. The structured algorithms are for an optimum torque generation and eventually controlling the satellite attitudes (roll/yaw) and nutation using a proportional (P) controller as well as managing the excess angular momentum via a proportional-integral (PI) controller. The developed control algorithms were tested using the complex and simplified geomagnetic field models for a LEO satellite mission in a nominal attitude operation. Their attitude torque generation performances were compared and it is found that the optimum torques can be generated by both the developed control algorithms. However, the system with three magnetic torquers provides a better torque generation compartment and consequently gives a better attitude performance up to 0.5 deg

ACS Style

Nurulasikin Mohd Suhadis; Renuganth Varatharajoo. A study of coupled magnetic fields for an optimum torque generation. The International Journal of Multiphysics 2012, 6, 73 -88.

AMA Style

Nurulasikin Mohd Suhadis, Renuganth Varatharajoo. A study of coupled magnetic fields for an optimum torque generation. The International Journal of Multiphysics. 2012; 6 (1):73-88.

Chicago/Turabian Style

Nurulasikin Mohd Suhadis; Renuganth Varatharajoo. 2012. "A study of coupled magnetic fields for an optimum torque generation." The International Journal of Multiphysics 6, no. 1: 73-88.

Journal article
Published: 01 December 2011 in The International Journal of Multiphysics
Reads 0
Downloads 0

This paper extends the previous works that appears in the International Journal of Multiphysics, Varatharajoo, Salit and Goh (2010). An approach incorporating cohesive zone modelling technique is incorporated into an optimized flywheel to properly simulate the stresses at the layer interfaces. Investigation on several fiber stacking sequences are also conducted to demonstrate the effect of fiber orientations on the overall rotor stress as well as the interface stress behaviour. The results demonstrated that the rotor interlaminar stresses are within the rotor materials' ultimate strength and that the fiber direction with a combination of 45°/-45°/0° offers the best triple layer rotor among the few combinations selected for this analysis. It was shown that the present approach can facilitate also further investigation on the interface stress behaviour of rotating rotors

ACS Style

Chong Lian; Renuganth Varatharajoo; Nurulasikin Mohd Suhadis. Interlaminar stress analysis for carbon/epoxy composite space rotors. The International Journal of Multiphysics 2011, 5, 353 -376.

AMA Style

Chong Lian, Renuganth Varatharajoo, Nurulasikin Mohd Suhadis. Interlaminar stress analysis for carbon/epoxy composite space rotors. The International Journal of Multiphysics. 2011; 5 (4):353-376.

Chicago/Turabian Style

Chong Lian; Renuganth Varatharajoo; Nurulasikin Mohd Suhadis. 2011. "Interlaminar stress analysis for carbon/epoxy composite space rotors." The International Journal of Multiphysics 5, no. 4: 353-376.