一种IBC桨叶控制用电动伺服电机系统的设计方法
By optimizing the design methodology of the motor system, decomposing the motor parameters according to the aircraft's response frequency, and optimizing the design of the rotor and stator, the problems of long design cycle and low matching degree of the motor system were solved, achieving efficient matching between the motor and the aircraft and reducing vibration.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHENZHEN UNITED AIRCRAFT TECH CO LTD
- Filing Date
- 2025-08-14
- Publication Date
- 2026-07-17
AI Technical Summary
In the existing technology, the electric servo motor system for IBC blade control has a long design cycle, low matching degree between the motor system and the blade and the aircraft, and difficulty in achieving physical isolation, magnetic isolation, thermal isolation and electrical isolation.
By decomposing the response frequency requirements of the motor system according to the aircraft's response frequency index, calculating the size and density parameters of the rotor and stator, establishing a motor model and database, optimizing the design parameters of the rotor and stator to meet the response frequency and matching requirements of the motor system, and optimizing the motor structure by setting appropriate rotational inertia ratios and air gap parameters.
It shortened the design cycle, improved the matching degree between the motor system and the aircraft, reduced the vibration of the propeller blades, improved the efficiency and applicability of the motor, and enhanced the dynamic response and dynamic adaptability of the motor and the aircraft.
Smart Images
Figure CN120793196B_ABST