Abstract
With the rapid development of technology, motors have drawn increasing attention in aviation applications, especially in the more electrical aircraft and all electrical aircraft concepts. Power weight ratio and reliability are key parameters for evaluating the performance of equipment applied in aircraft. The temperature rise of the motor is closely related to the reliability of the motor. Therefore, based on Taguchi, a novel multi-objective optimization method for the heat dissipation structural design of an electro-hydrostatic actuator (EHA) drive motor was proposed in this paper. First, the thermal network model of the EHA drive motor was established. Second, a sensitivity analysis of the key parameters affecting the cooling performance of the motor was conducted, such as the thickness of fins, the height of fins, the space of fins, the potting materials and the slot fill factor. Third, taking the average temperature of the windings and the power weight ratio as the optimization goal, the multi-objective optimal design of the heat dissipation structure of the motor was carried out by applying Taguchi. Then, a 3-D finite element model of the motor was established and the steady state thermal analysis was carried out. Furthermore, a prototype of the optimal motor was manufactured, and the temperature rise under full load condition tested. The result indicated that the motor with the optimized heat dissipating structure presented a low temperature rise and high power weight ratio, therefore validating the proposed optimization method.
Highlights
With the development of the more electric/all electric aircraft technology, aircraft servo-actuating systems are gradually developing from multi-energy source systems to a single electric power system [1]
Since a motor with low temperature and high power weight ratio can improve the performance of the actuating system, a novel multi-objective optimization method for heat dissipation structure design is presented in this paper
Where Fg is s a geometrical factor, g is the size of air gap, Dr is the diameter of the rotor, Ds is the diameter of the stator, ρ is the density of air, υ is the is the fluid kinematic viscosity, ω is the speed of the rotor and rm is the mean diameter of the air gap
Summary
With the development of the more electric/all electric aircraft technology, aircraft servo-actuating systems are gradually developing from multi-energy source systems to a single electric power system [1]. In order to improve the performance of the EHA drive motor, the power weight ratio and reliability of the motor should be enhanced. The existing research on the heat dissipation structure of an EHA drive motor has mainly focused on natural convection and wet-rotors where the air gap between the stator and rotor is filled with hydraulic oil [5]. Since a motor with low temperature and high power weight ratio can improve the performance of the actuating system, a novel multi-objective optimization method for heat dissipation structure design is presented in this paper. Using the Taguchi method, the optimum design of the heat dissipation structure was performed to choose the average temperature of the winding and the weight as optimization goals. The prototype with the optimized parameters was processed, and the temperature rise under different working conditions tested
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