Temperature rise is an important factor limiting the development of magnetic suspension support technology. Traditional temperature sensors such as thermocouples are complicated and vulnerable to electromagnetic interference due to their point contact temperature measurement methods. In this paper, the equivalent model of magnetic suspension support is established, and the temperature field is simulated and analyzed by magnetic thermal coupling calculation in ANSYS software. Then, a quasi-distributed temperature measurement system is designed, and the FBG temperature sensor is introduced to measure the temperature of the magnetic suspension support system by “one-line and multi-point”. By comparing the analysis experiments and simulations, the equivalent accuracy of the simulation model and the FBG temperature sensor can accurately measure the temperature of the magnetic suspension support.

Magnetic pole position detection is the core of the closed-loop control system of the permanent magnet linear synchronous motor (PMLSM), and its position estimation accuracy directly affects control performance and dynamic response speed. In order to solve the problem of the increased estimation error of magnetic pole position caused by magnetic field distortion at the end of PMLSM while also considering the cost of control hardware, the paper uses four linear Hall sensors as magnetic pole position detection components and adopts an optimized estimation algorithm to improve the dynamic performance of the motor. Firstly, a numerical simulation of the magnetic field of poles was conducted using Ansoft Maxwell software, and combined with theoretical analysis, the optimal installation position range of four linear Hall orthogonal placements relative to the motor was obtained. Meanwhile, based on the existing vector tracking position observer, an improved observer detection model is proposed. The Matlab/Simulink software was used to compare the Hall-based detection model with the Hall-based improved observer detection model, verifying the feasibility of the improved detection algorithm. Finally, the rationality of the spatial layout design of linear Hall and the feasibility of improving the estimation algorithm were verified through experiments.

This paper proposes a method to enhance the load capacity and reduce the volume of an Unmanned Aerial Vehicle (UAV) by optimizing the motor’s KV value (a measure of RPM per volt) to match the specific aerodynamic characteristics of a multi-blade propeller system. Given the fixed maximum output power of the motor when its volume and weight are determined, a higher-power-density motor structure can maximize blade lift by optimizing its output torque and speed. The electromagnetic structure of the motor is initially designed based on the aerodynamic characteristics of a 29-inch, four-blade model. Different motor Voltage-Turns (KV) value schemes are obtained by altering the number of winding turns and the wire diameter. Subsequently, the torque–speed output performance of the motor is calculated under constant power conditions. This data, in conjunction with the blade load, allow for a comparison of the motor’s output lift at different KV values. The optimal KV value for the motor is determined to be 116, resulting in a rated lift of 11.57 kg. This paper correctly analyzes the motor and blade as an integrated system, which is crucial for meaningful optimization in aerospace application.

Permanent magnet synchronous linear motor (PMSLM) has the advantages of simple mechanical structure and high thrust density. However, the simultaneous existence of end effect and cogging force aggravates the thrust ripple and affects the output characteristics of PMSLM. This paper proposes various rectangle and easily machinable auxiliary slots for core teeth to reduce thrust ripple. Firstly, the length, width and position of the auxiliary slot are parameterized by the finite element method, and the minimum detent force is solved to obtain the optimal slot size. Then, taking the air-gap flux density harmonic, average thrust and thrust ripple as reference indexes, the performance differences of the three auxiliary slots are compared. The results show that the auxiliary slot on the side of the tooth can reduce the thrust ripple by up to 22.4%, and the average thrust is only reduced by 3.7%. Finally, the correctness of the numerical simulation is verified by experiments.

Tip leakage degrades ducted fan performance and contributes to unsteady loading noise. This study investigates a wall-penetrating blade ring (WPBR) ducted fan for unmanned electric vertical takeoff and landing (eVTOL), replacing radial clearance with axial end face gaps. Six configurations of a 381 mm four-bladed rotor were evaluated at 5000 r/min under quasi-hover conditions: a conventional ducted fan, an internal blade ring rotor, and four WPBR cases with single-sided clearances of 0.8–2.0 mm. Sliding-mesh unsteady Reynolds-averaged Navier–Stokes simulations using the shear stress transport k-ω model were coupled with the Ffowcs Williams–Hawkings formulation. The WPBR formed a U-shaped cavity recirculation and redistributed the concentrated tip-region vortical structures. The 1.2 mm case retained 28.72 N of thrust, 2.1% above baseline, while reducing torque by 6.1% relative to the 0.8 mm case; its figure of merit remained lower. Its simulations predicted a reduction of 16.4 dB in the first blade-passing frequency level in the rotor plane and a predicted reduction of up to 15 dB in overall sound pressure level at 1 m. Thus, it represents a compromise among thrust, torque, and predicted acoustic performance rather than an aerodynamic optimum. A magnetically supported prototype operated up to 2000 r/min, demonstrating low-speed operability of the architecture for unmanned eVTOL propulsion.