Browsing by Author "Mukherjee, Bijoy Krishna"

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Adaptive block backstepping control for a UAV performing lateral maneuvers under lateral c.g. uncertainty
(Emerald, 2022-03) Mukherjee, Bijoy Krishna
Unmanned aerial vehicles (UAVs) have wide applications in surveillance and reconnaissance without risking human life. Due to unbalanced payload distribution or in-flight deployment, UAVs may undergo lateral center of gravity (c.g.) variations resulting in an asymmetric dynamic having significant longitudinal and lateral/directional coupling and hence more pronounced nonlinearity. Therefore, automatic control of UAVs becomes extremely difficult when it is forced to perform maneuvers under such imbalance in lateral mass distribution. The purpose of this paper is to design adaptive nonlinear control so that the UAV can perform some useful lateral/directional maneuver under lateral c.g. uncertainty.
Adaptive Fault-Tolerant Coulombic Satellite Attitude Control
(scribd, 2015) Mukherjee, Bijoy Krishna
Angular rate stabilization using fixed-time continuous sliding mode control
(IEEE, 2019) Mukherjee, Bijoy Krishna
This paper proposes a novel fault-tolerant control algorithm for angular rate stabilization of satellite system. The control algorithm belongs to the class of super-twisting sliding mode control theorem applicable to relative degree one systems which ensures chattering free control input and also finite-time convergence. Lyapunov stability theorem is used to prove finite-time stability of the closed loop system under designed control input. The expression of convergence time is calculated and is found to be independent of initial conditions. Numerical simulations verify the effectiveness of the proposed control algorithm.
Automatic recovery of a combat aircraft from a completed Cobra and Herbst maneuver: A sliding mode control based scheme
(IEEE, 2016) Mukherjee, Bijoy Krishna
Cobra and Herbst are two complex post-stall air combat maneuvers popularly executed by the present-day fighter aircraft. At the end of these maneuvers, the aircraft usually develops either a high negative flight path angle or a high negative flight path angle rate apart from a considerably low velocity. Therefore, the aircraft needs to recover from such undesired flight conditions as quickly as possible. Usually this recovery is achieved manually by the pilot. In the present paper, a novel automatic recovery strategy is proposed. Two recovery schemes - a partial recovery scheme to get back to a level flight condition quickly without worrying about velocity and a full recovery scheme to restore the initial steady level trim completely (both velocity and altitude wise) are presented. As these maneuvers are executed in high angle of attack regions, the aircraft flight dynamics becomes highly nonlinear and coupled requiring use of nonlinear control methods. In the present work, sliding mode control technique is considered as, apart from handling the nonlinearities effectively, it also provides robustness to uncertainty in the aerodynamic data. MATLAB simulation results are presented to first demonstrate the execution of the maneuvers and thereafter to validate the proposed recovery schemes.
Design, Fabrication, DSP Implementation and Comparison of Simulated Performance of a Linear Induction Motor for PI and Hα Control Schemes
(Maglev, 2004-10) Mukherjee, Bijoy Krishna
From conveyors to the high-speed MAGLEV vehicles, from knitting machines to the sophisticated robotic systems, Linear Induction Motors (LIMs) have got a wide range of applications. They have got all the potential to replace the age-old belt-pulley driven systems completely in the coming years. In the present work, a flat, single sided, short primary LIM, which can be used as a linear propulsion system, has been designed and the same has been fabricated. Thereafter PI controllers are designed to implement the field oriented control scheme for use in variable speed drives. The whole system is simulated in the SIMULINK environment of MATLAB and the simulation results are shown. Since the PI controllers cannot handle model uncertainties and parameter variation effects, a robust controller has also been designed. Implementation of the whole scheme is to be done using a DSP in TMS320LF2407A platform. Dry run of the programs has already been done. The inverter is under construction.
Design, fabrication, testing and finite element analysis of a lab-scale LIM
(IEEE, 2004-12) Mukherjee, Bijoy Krishna
Linear induction motors (LIMs) have got potential to replace the age old belt-pulley driven systems and the likes, which are in use for conversion of rotary to linear motion in most of the applications. In the present work a 3-phase, 50 Hz, 4-pole, 220 V, 320 W, 2.5 m/s LIM has been designed, fabricated and successfully tested on a test track. 2-D finite element analysis of the LIM has been done with ANSYS 7.1 to evaluate typical field and circuit variables. The results are in good agreement with the analytical as well as experimental values.
Dynamic Inversion Control for Performing Herbst Manoeuver with Lateral Center-of-Gravity Offset
(DSR, 2017) Mukherjee, Bijoy Krishna
The present study addresses the effects of lateral center-of-gravity (CG) movement, resulting from asymmetric firing of some of the onboard stores, on the dynamics and control of a combat aircraft while attempting the highly demanding Herbst manoeuver. The complete six degree-of-freedom equations of motion of the aircraft for such lateral CG offset are derived in two different body reference frames attached either to the symmetric nominal CG location or to the shifted asymmetric CG location. The Herbst manoeuver is first simulated using nonlinear dynamic inversion based control to handle the highly nonlinear post stall flight dynamics considering the standard equation of motion without considering any lateral CG variation. Thereafter, it is observed that if the same controller is retained, the manoeuver performance deteriorates significantly even when the CG undergoes a moderate lateral shift. To overcome this shortfall, closed loop controllers are next designed incorporating both the models of asymmetric dynamics as derived in this paper. It is validated through MATLAB simulations that both the controls, thus designed, can recover the original manoeuver performance almost completely; however, the first one requires more complex computations and hence increased computation time while the second one requires that all the measurements be transformed to the new body reference frame at every time step.
Exploiting Fractional Order PID Controller Methods in Improving the Performance of Integer Order PID Controllers: A GA Based Approach
(AIP, 2009-10) Mukherjee, Bijoy Krishna
The paper is divided into three parts. The first part gives a brief introduction to the overall paper, to fractional order PID (PIλDμ) controllers and to Genetic Algorithm (GA). In the second part, first it has been studied how the performance of an integer order PID controller deteriorates when implemented with lossy capacitors in its analog realization. Thereafter it has been shown that the lossy capacitors can be effectively modeled by fractional order terms. Then, a novel GA based method has been proposed to tune the controller parameters such that the original performance is retained even though realized with the same lossy capacitors. Simulation results have been presented to validate the usefulness of the method. Some Ziegler‐Nichols type tuning rules for design of fractional order PID controllers have been proposed in the literature [11]. In the third part, a novel GA based method has been proposed which shows how equivalent integer order PID controllers can be obtained which will give performance level similar to those of the fractional order PID controllers thereby removing the complexity involved in the implementation of the latter. It has been shown with extensive simulation results that the equivalent integer order PID controllers more or less retain the robustness and iso‐damping properties of the original fractional order PID controllers. Simulation results also show that the equivalent integer order PID controllers are more robust than the normal Ziegler‐Nichols tuned PID controllers.
Extreme aircraft maneuver under sudden lateral CG movement: Modeling and control
(Elsevier, 2017-09) Mukherjee, Bijoy Krishna
Hitherto unaddressed issue of six degree-of-freedom transient dynamics during asymmetric ejection of stores with finite velocity, onboard a combat aircraft, is addressed and modeled from the first principle. Further, the effect of asymmetric center-of-gravity shift, post ejection of the store, on some complex high angle-of-attack maneuvers such as cobra and Herbst is also investigated. It is shown that the performance of the maneuvers drastically deteriorates when carried out with controller designed for the pre-ejection symmetric . based dynamics. In order to improve the deteriorated performance, two new control schemes based on the standard sliding mode technique are proposed. The first sliding control is designed based on a simple ad-hoc model for the asymmetric dynamics, whereas the states are propagated using the exact model developed. It is shown that using this scheme the lost maneuver performance can be reasonably recovered. The second control scheme is formulated using an accurate asymmetric dynamics. This proposed control scheme almost completely recovers the original maneuver performance.
Forecast-based modeling and robust frequency control of standalone microgrids considering high penetration of renewable sources
(Wiley, 2020-12) Bhanot, Surekha; Mathur, Hitesh Datt; Mukherjee, Bijoy Krishna
This article proposes forecast-based modeling and robust frequency control strat-egy in isolated microgrids (MGs) to improve its stability. The intermittency andvariability in renewable generation is problem for its smooth integration to MGsconsidering frequency stability. Continuous rise in penetration levels of renew-able energy sources (RESs) is the main motivation behind forecast-based model-ing and controller design for MGs. The disturbances that affect the frequency inthe MG may come from the load side and/or the generation sides. In MGs, atthe generation side, the forecast of power from RESs is usually obtained to get arough estimate of available renewable power. The forecasted power always dif-fers from the actual one, so the secondary frequency controller may get over-burdened due to forecast error resulting in abnormal frequency deviation thatmay lead to unstable power system. The proposedH∞based robust controldesign considers the forecast error which improves the system stability and per-formance against disturbances coming from load/generation side.
Fractional Order Modeling and GA Based Tuning for Analog Realization with Lossy Capacitors of a PID Controller
(IMECS, 2009-03) Mukherjee, Bijoy Krishna
In this paper, first it has been studied how the performance of a PID controller deteriorates when implemented with lossy capacitors in its analog realization. Thereafter it has been shown that the lossy capacitors can be effectively modeled by fractional order terms. Finally, a novel GA based method has been proposed to tune the controller parameters such that the original performance is retained even though realized with the same lossy capacitors. Simulation results have been presented to validate the usefulness of the technique.
Modeling and Bifurcation Analysis of Combat Aircraft Dynamics under Lateral C.M. Shift
(ARC, 2016-01) Mukherjee, Bijoy Krishna
Nonlinear dynamics and control of a laterally mass varying fighter aircraft
(Sage, 2017-08-14) Mukherjee, Bijoy Krishna
This paper presents dynamic analysis and nonlinear control of laterally mass varying combat aircraft based on a six degree-of-freedom model derived for a variable mass system. The objective is to investigate the effects of asymmetric lateral mass variation, due to mass ejection, from two different perspectives – the open loop dynamic behavior through bifurcation analysis; and the closed loop control performance while carrying out some demanding maneuvers. Bifurcation analysis reveals considerable coupling between the longitudinal and lateral-directional channels even for a modest lateral shift in the center-of-mass due to store ejection, which in turn is observed to give rise to a spiral-dive like divergent mode even at low angles-of-attack. Thereafter, the well-known high angle-of-attack cobra maneuver is implemented for the symmetric center-of-mass case using sliding mode control technique and using a new single loop control formulation in contrast with the conventional inner-outer loop formulation. The proposed single loop control formulation is further extended to handle the lateral movement of center-of-mass due to asymmetric store ejection using the asymmetric dynamics model proposed and derived in this paper.
Performance assessment of a distribution system by simultaneous optimal positioning of electric vehicle charging stations and distributed generators
(Elsevier, 2023-01) Mathur, Hitesh Datt; Mishra, Puneet; Mukherjee, Bijoy Krishna
Extensive penetration of Renewable Energy based Distributed Generator (REDG) units in a Distribution System necessitates its efficient and optimal applicability. Plug-in Electric Vehicles (PEV) is currently gaining importance steadily in a distribution system due to its environmental compatibility. However, suitable positioning of PEV is a mandate as it increases the overall demand of the system and has appreciable impact on the system's technical performance in terms of losses, voltage profile, penetration level, to name a few. This paper proposes a simple apparent power loss driven technique of Electric Vehicle Charging Station (EVCS) placement along with a REDG unit in a distribution system taking time-driven load models into consideration. The initial State of Charge of the PEV is reformulated taking traffic and weather conditions, proportional distance covered by the electric vehicle and non-availability of EVCS into consideration using Dynamic Fault Tree Analysis and Bayesian optimization techniques. An optimum combination of different sets of PEV with proportional distance coverage is considered. Results are validated on the basis of computation of three REDG assessment indices in comparison with an arbitrary slot of positioning of the above elements
Real-Time Air Quality Estimation from Station Data Using Extended Fractional Kalman Filter
(Springer, 2020-07) Mukherjee, Bijoy Krishna
Air, soil and water pollutions have the greatest risk factors for human health. There are different types of air pollutants which are emitted from human activities. One of these pollutants is nitrogen dioxide (NO2) which is produced from fossil fuel-based energy and use of motor vehicles. Since India is facing deteriorated air quality due to economic development, air quality management is becoming a real challenge. In 2015, an emission inventory (EI) was developed for India with 2015 as the base year. This EI is developed on an engineering model approach which is based on a technology-linked energy emission modeling approach. Accurate EI is important for future air quality modeling and air quality management. Since EI has uncertainties in data, some kind of estimation is essential. Estimation through extended fractional Kalman filter (EFKF) is considered in the present paper, and its performance is found to be superior as compared to a standard extended Kalman filter (EKF).
Three-Axis Global Magnetic Attitude Control of Earth-Pointing Satellites in Circular Orbit
(Wiley, 2017-03) Mukherjee, Bijoy Krishna
This paper addresses the controllability and global stability issues of a magnetically actuated satellite in the geomagnetic field. The variation of the geomagnetic field along the orbit, which is time varying in nature, makes the dynamics of the satellite time varying also. Sufficient conditions for controllability of such a time varying magnetic attitude control system are given. As a major contribution, it is proven that the three-axis controllability of the spacecraft actuated by the magnetic actuators is possible and it does not depend on the initial angular velocity of the spacecraft. Global controllability is a precursor to global stability. Therefore, exponential stability for an arbitrarily high initial angular velocity and an arbitrary initial orientation is proven next for a proportional-derivative control law using averaging theory. It is also proven that even an iso-inertial satellite can be stabilized using the time invariant feedback control, which was hitherto not possible, even using time variant conventional control. Simulation results are presented under different initial orientations and angular velocities of the satellite in the presence of favorable and unfavorable gravity gradient torques to validate the proposed control method.