No abstract

Power electronic converters find application in diverse fields due to their high power conversion efficiency. Converters are often characterized by time response specifications, robustness and stability. Conventionally, converters employ the classic PID controller. The state space average linear time invariant model of a boost converter is known to be a non-minimum phase system. This paper demonstrates that the boost converter with a PID controller using the Queen Bee assisted Genetic Algorithm (QBGA) optimization is not robust to plant parameter variations. A fractional order PID controller based on QBGA optimization proposed here is shown to have improved robustness. The controller proposed here is applicable across converters, viz., buck, boost and buck-boost, equally.

This paper presents simulation and hardware implementation of Three Phase Three Level Shunt Active Power Filter to mitigate the supply current harmonics and inject the required reactive power to non-linear loads. The standard operating principle of shunt active filter is to inject current harmonics into the point of common coupling. This scheme consists of three phase three level diode clamped multilevel inverter which can be used to reduce the source current harmonics. The proposed pulse width modulation (PWM) scheme generates the inverter leg switching times, from the sampled reference phase voltage amplitudes and centres the switching times for the middle vectors, in a sampling interval, as in the case of conventional space vector PWM (SVPWM). Effectiveness of the system is verified by the experimental results obtained from the prototype model.

The article presents an Aircraft Indoor Wireless Network (AIWN) model with multi-sensor antenna sequence algorithm that replaces existing indoor wired sensor network in aircraft with wireless sensor network to reduce electrical wiring issues. The proposed aircraft indoor radio transmission of signals from multiple wireless sensors and the space division multiple access technique increases the strength of transmission power and reduces the electromagnetic signal interference. The performance of proposed AIWN model is investigated and validated for aircraft indoor wireless sensor communication. This model controls the aircraft performance and improves the overall capacity of the aircraft indoor wireless system.

Abstract:The orientation of a satellite in space described relative to some other object or system is known as the attitude of the satellite. The attitude may be changing with time. To be able to control the attitude of the satellite, it must be equipped with actuators that can produce the required torque. Control Moment Gyroscope is a space craft control actuator which acts as torque amplifier. It is suitable for three axis slew manoeuvring by providing the necessary torques via gimbaling a spinning flywheel. Control Moment Gyroscope is considered to be more efficient in terms of power consumption and slew rate. A major drawback encountered with the use of the Control Moment Gyroscope is the possibility of singularities for certain combinations of gimbal angles. The objective of this work is to detect these singularities so that robust steering laws can be developed.