Naba peyada | IIT Kharagpur (original) (raw)

Papers by Naba peyada

Journal of the Franklin Institute, 2020

HLA-B27 frequency in a group of patients with psoriatic arthritis * Freqüência de HLA-B27 em uma ... more HLA-B27 frequency in a group of patients with psoriatic arthritis * Freqüência de HLA-B27 em uma amostra de pacientes com artrite psoriática

Elsevier, 2020

This work investigates the semi-global tracking control of a class of uncertain nonlinear systems... more This work investigates the semi-global tracking control of a class of uncertain nonlinear systems with
input saturation, using adaptive backstepping controller and tuning function design. The control input
has been represented as a product of a positive constant and a generalized saturation function of unit
magnitude, where the constant parameter represents the saturation bound of the available input signal. It
has been shown that the overall saturation problem can be realized as an equivalent problem involving no
saturation if the system satisfies a sufficient condition. The condition represents a relationship between
the saturation bound of the input signal and the upper bounds of tracking errors, disturbances, and
uncertainties. To realize this fact physically, the proposed control algorithm has been implemented on a
Twin Rotor Multi Input Multi Output System (TRMS). Experimental and simulation outcomes illustrate
the validation of the derived control methodology along with robustness and performance analysis.
© 2020 The Franklin Institute. Published by Elsevier Ltd. All rights reserved.
∗ Corresponding author.
E-mail address: manabesh.panda@aero.iitkgp.ac.in (M. Panda).
https://doi.

— Parameter estimation technique is an indispensable computational tool not only in aerospace res... more — Parameter estimation technique is an indispensable computational tool not only in aerospace research activities but also industrial activities such as control law design, handling qualities evaluation, model validation, and flight-vehicle design and certification. The estimation methods yield different levels of associated error with the estimated parameters. The primary reason for this is linked to the presence of measurement and process noise with the real flight data. Equation Error Method cannot handle either process noise or measurement noise. Output Error Method can handle measurement noise but not process noise. Filter Error Method, a special case of Output Error method, can be advantageously used to estimate parameter from flight data having both process and measurement noise. This paper presents issues related to the application of FEM with Gauss Newton (GN) and Levenberg-Marquardt (LM) optimization in estimating aerodynamic parameters from in-house generated flight data.

The system identification is a broad area of research in various fields of engineering. Among the... more The system identification is a broad area of research in various fields of engineering. Among them, our concern is to identify the aircraft dynamics by means of the measured motion and control variables using a new approach which is based on the support vector machine (SVM) regression. Due to the computational complexity of SVM, it is suggested to adopt the advanced version of SVM i.e. least square support vector machine (LSSVM) to be used for system identification. LSSVM regression is a network-based approach which requires a user defined kernel function and a set of input-output data for its training before the prediction phase like a neural-network (NN) based procedure. In this paper, LSSVM regression has been used to identify the non-linear dynamics of aircraft using real flight data.

Application of adaptive neuro fuzzy inference system (ANFIS)-based particle swarm optimization (P... more Application of adaptive neuro fuzzy inference system (ANFIS)-based particle swarm optimization (PSO) algorithm to the problem of aerodynamic modeling and optimal parameter estimation for aircraft has been addressed in this chapter. The ANFIS-based PSO optimizer constitutes the aircraft model in restricted sense capable of predicting generalized force and moment coefficients employing measured motion and control variables only, without formal requirement of conventional variables or their time derivatives. It has been shown that such an approximate model can be used to extract equivalent stability and control derivatives of a rigid aircraft.

Aerial robotics is a growing field with tremendous civil and military applications. Potential app... more Aerial robotics is a growing field with tremendous civil and military applications. Potential applications include surveying and maintenance tasks, aerial transportation and manipulation, search and rescue, and surveillance. The challenges associated with tackling robotics tasks in complex, three dimensional, indoor and outdoor environments bring into focus some of the limitations of accepted solutions to classical robotics problems in sensing, planning, localization, and mapping. A quadcopter which is capable of autonomous landing on a stationary platform using only onboard parameters such as sensing, recognition and computation is presented. We present state-of-the-art computer vision, deep learning neural net inception model, algorithms, detection and state estimation of the target for our project. We have deployed and tested in indoor environment due to limitations of resources and controlled environmental features. We rely on Faster-RCNN-Inception-V2-COCO model but other robust...

Aircraft Engineering and Aerospace Technology

Purpose The purpose of this paper is to investigate the estimation methodology with a highly gene... more Purpose The purpose of this paper is to investigate the estimation methodology with a highly generalized cost-effective single hidden layer neural network. Design/methodology/approach The aerodynamic parameter estimation is a challenging research area of aircraft system identification, which finds various applications such as flight control law design and flight simulators. With the availability of the large database, the data-driven methods have gained attention, which is primarily based on the nonlinear function approximation using artificial neural networks. A novel single hidden layer feed-forward neural network (FFNN) known as extreme learning machine (ELM), which overcomes the issues such as learning rate, number of epochs, local minima, generalization performance and computational cost, as encountered in the conventional gradient learning-based FFNN has been used for the nonlinear modeling of the aerodynamic forces and moments. A mathematical formulation based on the partial ...

Computational Materials Science

Abstract Although Ngo et al. (2006) determined the Young’s modulus and ultimate strength of Ge na... more Abstract Although Ngo et al. (2006) determined the Young’s modulus and ultimate strength of Ge nanowires experimentally by using atomic force microscopy, orientation dependent these properties, its loading tip velocity dependent mechanical properties were not determined due to limitations of the experimental procedures. They did not visualize and explain the reasons behind their brittle fracture. Another limitation in their experimental study was that they were not able to carry out the experiment considering the diameters of nanowires below 20 nm. In the present study we model the nanowires following the experimental procedure in the range of diameter 1–30 nm using molecular dynamic simulation. Firstly, we verify the present theoretical results comparing with those of experimental studies to prove the validity of the present study. Then we calculate the orientation and indenter velocity dependent these properties. We visualize the phase change of its loading region during bending to understand their brittle fracture. The comparative study of the mechanical properties of Ge-core/Si-shell and Si-core/Ge-shell nanowires as a function of temperature are studied. Effects of temperatures and indenter velocity on the mechanical properties of Ge-Si nanowires are also studied.

AIAA Atmospheric Flight Mechanics Conference, 2016

Two types of the new wing design concept, namely the ventilated flapping wing have been proposed.... more Two types of the new wing design concept, namely the ventilated flapping wing have been proposed. It focuses on “ventilating” the wing during the upstroke motion so as to reduce the negative lift while increasing the net positive lift at each flapping cycle. The presence of the moving flaps can actually modify the flow pattern of the flapping wing significantly comparing with the solid wing case. The opening flaps can effectively increase the frontal areas in the airflow direction causing higher drag but at the same time generate lower negative lift during the upstroke. The vortical structures in the chordwise and spanwise directions at different positions together with the force variations around the wing have been obtained computationally and analyzed in details.

Journal of Guidance, Control, and Dynamics, 2013

This article proposes a scheme to estimate the aerodynamic derivatives of aircraft using a wind t... more This article proposes a scheme to estimate the aerodynamic derivatives of aircraft using a wind tunnel dynamic test rig system. A five-degree-of-freedom (DOF) rig system has been used to simulate near free flight manoeuvres inside the wind tunnel by exciting a scaled down model aircraft through various types of control surface deflections. A mathematical model that incorporates five DOF in aircraft motion has been developed. The five DOF equations of motion of the rig system are formulated using a vector and matrix approach. The simulated flight data, generated from a five DOF mathematical model, has been used to estimate the aerodynamic parameters of the aircraft. The maximum likelihood method has been used to achieve close estimates of the parameters by minimizing the error between simulated and computed response.

Aircraft Parameter estimation is probably the most outstanding and illustrated example of the sys... more Aircraft Parameter estimation is probably the most outstanding and illustrated example of the system identification methodology. In the past the most widely used parameter estimation methods have been Equation error method, Output error method, Maximum likelihood method and Filter error method. In this paper an algorithm based on neural modeling and Gauss-Newton optimization is proposed to estimate aerodynamic parameters from flight data. The proposed method bypasses the requirement of solving the equations of motion to predict motion variables. The proposed algorithm uses a black box approach to build the flight dynamic model of an aircraft using measured flight variables. The algorithm was initially validated on flight data generated using HANSA-3 aircraft at Indian Institute of Technology Kanpur. Similar validation was carried out with lateral-directional flight data of ATTAS aircraft (supplied by DLR Germany). The estimated values were compared with estimates obtained using Filter error method and Least square method. The applicability of the proposed algorithm in handling flight data with atmospheric turbulence was also investigated by applying it on real flight data of test aircraft, HFB-320. The work concludes by presenting a comparison among the estimates obtained by applying several methods on real flight data of three different test aircraft.

Parafoil and payload system are light weight, fly at low speed and provides soft landing capabili... more Parafoil and payload system are light weight, fly at low speed and provides soft landing capability. The parafoil-payload system flight dynamics requires a 9-DOF model unlike the 6-DOF model, since this system is a two-body dynamic system. This paper attempts to ...

Journal of the Franklin Institute, 2020

HLA-B27 frequency in a group of patients with psoriatic arthritis * Freqüência de HLA-B27 em uma ... more HLA-B27 frequency in a group of patients with psoriatic arthritis * Freqüência de HLA-B27 em uma amostra de pacientes com artrite psoriática

Elsevier, 2020

This work investigates the semi-global tracking control of a class of uncertain nonlinear systems... more This work investigates the semi-global tracking control of a class of uncertain nonlinear systems with
input saturation, using adaptive backstepping controller and tuning function design. The control input
has been represented as a product of a positive constant and a generalized saturation function of unit
magnitude, where the constant parameter represents the saturation bound of the available input signal. It
has been shown that the overall saturation problem can be realized as an equivalent problem involving no
saturation if the system satisfies a sufficient condition. The condition represents a relationship between
the saturation bound of the input signal and the upper bounds of tracking errors, disturbances, and
uncertainties. To realize this fact physically, the proposed control algorithm has been implemented on a
Twin Rotor Multi Input Multi Output System (TRMS). Experimental and simulation outcomes illustrate
the validation of the derived control methodology along with robustness and performance analysis.
© 2020 The Franklin Institute. Published by Elsevier Ltd. All rights reserved.
∗ Corresponding author.
E-mail address: manabesh.panda@aero.iitkgp.ac.in (M. Panda).
https://doi.

— Parameter estimation technique is an indispensable computational tool not only in aerospace res... more — Parameter estimation technique is an indispensable computational tool not only in aerospace research activities but also industrial activities such as control law design, handling qualities evaluation, model validation, and flight-vehicle design and certification. The estimation methods yield different levels of associated error with the estimated parameters. The primary reason for this is linked to the presence of measurement and process noise with the real flight data. Equation Error Method cannot handle either process noise or measurement noise. Output Error Method can handle measurement noise but not process noise. Filter Error Method, a special case of Output Error method, can be advantageously used to estimate parameter from flight data having both process and measurement noise. This paper presents issues related to the application of FEM with Gauss Newton (GN) and Levenberg-Marquardt (LM) optimization in estimating aerodynamic parameters from in-house generated flight data.

The system identification is a broad area of research in various fields of engineering. Among the... more The system identification is a broad area of research in various fields of engineering. Among them, our concern is to identify the aircraft dynamics by means of the measured motion and control variables using a new approach which is based on the support vector machine (SVM) regression. Due to the computational complexity of SVM, it is suggested to adopt the advanced version of SVM i.e. least square support vector machine (LSSVM) to be used for system identification. LSSVM regression is a network-based approach which requires a user defined kernel function and a set of input-output data for its training before the prediction phase like a neural-network (NN) based procedure. In this paper, LSSVM regression has been used to identify the non-linear dynamics of aircraft using real flight data.

Application of adaptive neuro fuzzy inference system (ANFIS)-based particle swarm optimization (P... more Application of adaptive neuro fuzzy inference system (ANFIS)-based particle swarm optimization (PSO) algorithm to the problem of aerodynamic modeling and optimal parameter estimation for aircraft has been addressed in this chapter. The ANFIS-based PSO optimizer constitutes the aircraft model in restricted sense capable of predicting generalized force and moment coefficients employing measured motion and control variables only, without formal requirement of conventional variables or their time derivatives. It has been shown that such an approximate model can be used to extract equivalent stability and control derivatives of a rigid aircraft.

Aerial robotics is a growing field with tremendous civil and military applications. Potential app... more Aerial robotics is a growing field with tremendous civil and military applications. Potential applications include surveying and maintenance tasks, aerial transportation and manipulation, search and rescue, and surveillance. The challenges associated with tackling robotics tasks in complex, three dimensional, indoor and outdoor environments bring into focus some of the limitations of accepted solutions to classical robotics problems in sensing, planning, localization, and mapping. A quadcopter which is capable of autonomous landing on a stationary platform using only onboard parameters such as sensing, recognition and computation is presented. We present state-of-the-art computer vision, deep learning neural net inception model, algorithms, detection and state estimation of the target for our project. We have deployed and tested in indoor environment due to limitations of resources and controlled environmental features. We rely on Faster-RCNN-Inception-V2-COCO model but other robust...

Aircraft Engineering and Aerospace Technology

Purpose The purpose of this paper is to investigate the estimation methodology with a highly gene... more Purpose The purpose of this paper is to investigate the estimation methodology with a highly generalized cost-effective single hidden layer neural network. Design/methodology/approach The aerodynamic parameter estimation is a challenging research area of aircraft system identification, which finds various applications such as flight control law design and flight simulators. With the availability of the large database, the data-driven methods have gained attention, which is primarily based on the nonlinear function approximation using artificial neural networks. A novel single hidden layer feed-forward neural network (FFNN) known as extreme learning machine (ELM), which overcomes the issues such as learning rate, number of epochs, local minima, generalization performance and computational cost, as encountered in the conventional gradient learning-based FFNN has been used for the nonlinear modeling of the aerodynamic forces and moments. A mathematical formulation based on the partial ...

Computational Materials Science

Abstract Although Ngo et al. (2006) determined the Young’s modulus and ultimate strength of Ge na... more Abstract Although Ngo et al. (2006) determined the Young’s modulus and ultimate strength of Ge nanowires experimentally by using atomic force microscopy, orientation dependent these properties, its loading tip velocity dependent mechanical properties were not determined due to limitations of the experimental procedures. They did not visualize and explain the reasons behind their brittle fracture. Another limitation in their experimental study was that they were not able to carry out the experiment considering the diameters of nanowires below 20 nm. In the present study we model the nanowires following the experimental procedure in the range of diameter 1–30 nm using molecular dynamic simulation. Firstly, we verify the present theoretical results comparing with those of experimental studies to prove the validity of the present study. Then we calculate the orientation and indenter velocity dependent these properties. We visualize the phase change of its loading region during bending to understand their brittle fracture. The comparative study of the mechanical properties of Ge-core/Si-shell and Si-core/Ge-shell nanowires as a function of temperature are studied. Effects of temperatures and indenter velocity on the mechanical properties of Ge-Si nanowires are also studied.

AIAA Atmospheric Flight Mechanics Conference, 2016

Two types of the new wing design concept, namely the ventilated flapping wing have been proposed.... more Two types of the new wing design concept, namely the ventilated flapping wing have been proposed. It focuses on “ventilating” the wing during the upstroke motion so as to reduce the negative lift while increasing the net positive lift at each flapping cycle. The presence of the moving flaps can actually modify the flow pattern of the flapping wing significantly comparing with the solid wing case. The opening flaps can effectively increase the frontal areas in the airflow direction causing higher drag but at the same time generate lower negative lift during the upstroke. The vortical structures in the chordwise and spanwise directions at different positions together with the force variations around the wing have been obtained computationally and analyzed in details.

Journal of Guidance, Control, and Dynamics, 2013

This article proposes a scheme to estimate the aerodynamic derivatives of aircraft using a wind t... more This article proposes a scheme to estimate the aerodynamic derivatives of aircraft using a wind tunnel dynamic test rig system. A five-degree-of-freedom (DOF) rig system has been used to simulate near free flight manoeuvres inside the wind tunnel by exciting a scaled down model aircraft through various types of control surface deflections. A mathematical model that incorporates five DOF in aircraft motion has been developed. The five DOF equations of motion of the rig system are formulated using a vector and matrix approach. The simulated flight data, generated from a five DOF mathematical model, has been used to estimate the aerodynamic parameters of the aircraft. The maximum likelihood method has been used to achieve close estimates of the parameters by minimizing the error between simulated and computed response.

Aircraft Parameter estimation is probably the most outstanding and illustrated example of the sys... more Aircraft Parameter estimation is probably the most outstanding and illustrated example of the system identification methodology. In the past the most widely used parameter estimation methods have been Equation error method, Output error method, Maximum likelihood method and Filter error method. In this paper an algorithm based on neural modeling and Gauss-Newton optimization is proposed to estimate aerodynamic parameters from flight data. The proposed method bypasses the requirement of solving the equations of motion to predict motion variables. The proposed algorithm uses a black box approach to build the flight dynamic model of an aircraft using measured flight variables. The algorithm was initially validated on flight data generated using HANSA-3 aircraft at Indian Institute of Technology Kanpur. Similar validation was carried out with lateral-directional flight data of ATTAS aircraft (supplied by DLR Germany). The estimated values were compared with estimates obtained using Filter error method and Least square method. The applicability of the proposed algorithm in handling flight data with atmospheric turbulence was also investigated by applying it on real flight data of test aircraft, HFB-320. The work concludes by presenting a comparison among the estimates obtained by applying several methods on real flight data of three different test aircraft.

Parafoil and payload system are light weight, fly at low speed and provides soft landing capabili... more Parafoil and payload system are light weight, fly at low speed and provides soft landing capability. The parafoil-payload system flight dynamics requires a 9-DOF model unlike the 6-DOF model, since this system is a two-body dynamic system. This paper attempts to ...