A series expansion method aided design of current mode second generation current conveyor based active control circuit

Gupta, Preety; Verma, Vijay; Ranjan, Rajeev Kumar; Appasani, Bhargav; Priyadarshini, Bindu; Nath, Vijay

doi:10.1007/s00542-018-4117-6

Cited by 4 publications

(2 citation statements)

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“…Active control circuits based on second generation current conveyors, popularly referred to as CCIIs, have been widely adopted in the past few years [19]. CCII was used for the synthesis of transfer function [20], design of filters [21], oscillators [22,23], controllers [24][25][26], etc. In [24], CCII based active control circuit was experimentally demonstrated for a physical system, whose control parameters were obtained using a series expansion method.…”

Section: Introductionmentioning

confidence: 99%

“…CCII was used for the synthesis of transfer function [20], design of filters [21], oscillators [22,23], controllers [24][25][26], etc. In [24], CCII based active control circuit was experimentally demonstrated for a physical system, whose control parameters were obtained using a series expansion method. The same series expansion method was extended for designing CCII controllers for a two-input two-output (TITO) system in [25].…”

Section: Introductionmentioning

confidence: 99%

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A New Active Control Driver Circuit for Satellite’s Torquer System Using Second Generation Current Conveyor

et al. 2021

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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.

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