No abstract

No abstract

Electrical machines for aircraft applications require basic characteristics such as lightweight, high reliability, fault tolerance ability, and torque power and higher densities. Correspondingly, hybrid excitation flux switching machines (HE‐FSMs) are capable of producing significant characteristics of high torque and power by improving flux strengthening in the iron core. However, magnetic flux cancellation and leakage in HE‐FSMs cause the reduction of flux linkage created by permanent magnet (PM) and field excitation (FE), which leads to deterioration of electromagnetic torque. This study presents magnetic flux performance and comparison of various topologies of HE‐FSMs by employing different positions of PMs and FE coils on the stator core. The purpose of a segmented rotor is to deliver a well‐defined electromagnetic flux pathway for carrying magnetic flux to nearby armature coil on stator with rotor rotation to improve the flux strengthening. Moreover, magnetic performances of various proposed HE‐FSMs at different positions of PMs are investigated and compared based on 2D finite element analysis. Subsequently, the enhanced HE‐FSM III has successfully achieved flux strengthening of 22%, torque of 54% and power of 61% more than initial design of HE FSM I, respectively. In conclusion, the proposed HE‐FSM structures show the capability to match high torque and power for aircraft applications.

No abstract

Attitude Control System (ACS) is one of the critical subsystems of any spacecraft andtypically is in charge of de-tumbling, controlling and orienting the satellite after initial deployment and during the satellite operations. The magnetorquer is a core magnetic attitude control actuator and, therefore, a good choice for nanosatellite attitude stabilization. There are various methods to achieve control torque using the magnetorquer. An innovative design of printed magnetorquer has been proposed for the nanosatellites which is modular, scalable, cost effective, less prone to failure, with reduced harness and power consumption since the traces are printed either on top layer or inner layers of the printed circuit board. The analysis in terms of generated torque with a range of input applied voltages, trace widths, outer and inner-most trace lengths is presented to achieve the optimized design.The optimum operating voltage is selected to generate the desired torque while optimizing the torque to the power ratio. The results of analysis in terms of selection of optimized parameters including torque to power ratio, generated magnetic dipole moment and power consumption have been validated practically on a cubesat panel. The printed magnetorquer configuration is modular which is useful to achieve mission level stabilization requirements. For spin stabilized satellites, the rotation time analysis has been performed using the printed magnetorquer.