This article demonstrates a voltage differencing inverting buffered amplifier (VDIBA)-based resistorless flux-controlled memristor emulator circuit with tunability. Two VDIBA blocks serve as active components, and a grounded capacitor serving as a passive part. The proposed emulator design is devoid of multipliers and resistors through effective utilization of port relationships. Including tunability, the suggested emulator functions in both incremental and decremental modes. It accurately depicts the attributes of an ideal memristor up to 12.7 MHz and consumes a total power of 1.34 mW. The mathematical analysis is substantiated through Cadence simulation in 0.18- $\mu$ m Taiwan Semiconductor Manufacturing Company (TSMC) technology with the supply voltage of $\pm$ 1 V. Nonideal, single/parallel, Monte-Carlo sampling and corner analysis were conducted to confirm circuit resilience. The nonvolatile nature of the presented emulator model has also been included. A breadboard prototype incorporating the ICs CA3080 and LT1193 are built to conduct an experimental demonstration. The experimental findings were consistent with the theoretical expectations and simulation results.

This paper presents an optimized algorithm for event-triggered control (ETC) of networked control systems (NCS). Initially, the traditional backstepping controller is designed for a generalized nonlinear plant in strict-feedback form that is subsequently extended to the ETC. In the NCS, the controller and the plant communicate with each other using a communication network. In order to minimize the bandwidth required, the number of samples to be sent over the communication channel should be reduced. This can be achieved using the non-uniform sampling of data. However, the implementation of non-uniform sampling without a proper event triggering rule might lead the closed-loop system towards instability. Therefore, an optimized event triggering algorithm has been designed such that the system states are always forced to remain in stable trajectory. Additionally, the effect of ETC on the stability of backstepping control has been analyzed using the Lyapunov stability theory. Two case studies on an inverted pendulum system and single-link robot system have been carried out to demonstrate the effectiveness of the proposed ETC in terms of system states, control effort and inter-event execution time.

This research examines a torquer system for satellite attitude control which requires low energy, or average power, to control its moment. The magnetic torquer consists of an LR component, source and switching pulse. A mathematical model and design equations are presented for the magnetic torquer. A technique of using torquer system to do 3-axis spacecraft attitude control has been presented. The main goal of this system is to attain specific current control in the torquer system by means of CCII action. CCII is used since the full operation is performed in high frequency system. The closed loop control action of the controller, the triangular wave generator, CCII and torquer system are specific parameters used in this research. This scheme's performance has been considered via analysis and simulation model. The resulting closed-loop systems are robust with respect to parametric modeling ambiguity. The result attained by OrCAD PSPICE, belonging to Cadence design systems with respect to desired amount of current value proves the efficiency of the proposed research method.

In this article a new active control driver circuit is designed using the second-generation current conveyor for the satellite’s torquer system. The torquer plays an important role in the attitude control of the satellite. Based on the magneto-meter data, the satellite’s microprocessor calculates the required current for the torque and sends a reference command. A close loop control system is designed, which generates the desired output current. The parameters of the controller are optimized using a variant of the well-known evolutionary algorithm, the genetic algorithm (GA). This variant is known as the segmented GA. The controller is experimentally implemented using the commercially available integrated circuit, the AD844. The error between the experimental and simulation results has RMS values in range of 0.01–0.16 A for the output current and 0.41–0.6 V for the output voltage. It has mean value of 0.01 A for the output current and has mean values in the range of 0.33–0.48 V for the output voltage. It has standard deviation of 0.01 A for the output current and standard deviations in the range of 0.24–0.35 V for the output voltage. Thus, there is a close match between the simulation and experimental results, validating the design approach. These designs have many practical applications, particularly for nanosatellites powered by photovoltaic panels.