Based on the technical platform of electrically actuated nose wheel steering systems, a new type of damping shimmy reduction technology is developed to break through the limitations of traditional hydraulic damping shimmy reduction methods, and an electrically actuated nose wheel steering structure scheme is proposed. The mathematical model of the electromagnetic damper is established, the derivation of skin depth, damping torque and damping coefficient is completed, and the design of the shape and size of the electromagnetic damper is combined with the derivation results and the technical index of shimmy reduction. The electromagnetic field finite element simulation results show that the mathematical modeling method of the electromagnetic damper has good accuracy, and its application to the shimmy reduction module of the electrically actuated nose wheel steering system is also feasible and superior. Finally, the key factors influencing the performance of electromagnetic damper shimmy reduction are studied and analyzed, thus forming a complete electromagnetic damper shimmy reduction technology for the electrically actuated system, and laying the foundation for the design of novel all-electric aircraft and landing gear.

This paper investigates the search for architecture solutions to a novel shimmy reduction subsystem in the nose wheel steering system (NWSS) of all electric aircraft (AEA). Since the traditional trial-and-error and empirical methods are inefficient and infeasible in this study, respectively, a new methodology for system architecture design is needed. The integrated methodology combines the systems engineering engine method and V-model to explore the design space of the shimmy reduction subsystem, defines the parameters of the low-level product using general morphological analysis (GMA), eliminates incompatible alternatives through cross-consistency assessment (CCA), and, after morphological analysis, subjects the solutions that satisfy the optimal design set to a single-objective decision based on cost-effectiveness analysis (CEA). Furthermore, a product realization of the final selected design solution is presented, along with the implementation and verification processes. The methodology deals with the problem in the design of the shimmy reduction subsystem in AEA.

This article investigates the damping coefficients of electromagnetic dampers (EMDs) employed for shimmy reduction in the nose landing gear of all-electric aircraft (AEA). Parasitic damping exists in the shimmy reduction subsystem, which causes the actual damping coefficients to differ significantly from those calculated only using the electromagnetic model in previous studies. This difference will directly lead to dimensional redundancy in the structural design of EMD. By establishing the power flow of the shimmy reduction channel in this study, the components of parasitic damping are identified, and the corresponding loss models are then developed. When the damping coefficient, which considers parasitic damping, is applied to the structural design of EMD, the dimensional parameters may be greatly reduced while still satisfying the technical requirements and achieving the goal of lightweight aircraft. Finally, the comparison of the analysis with the experimental data demonstrates good agreement.