航空学报2026，Vol.47Issue(7)：351-366,16.DOI:10.7527/S1000-6893.2025.32464
直升机桨毂顶置主动式作动系统设计
Design of a hub-mounted active actuation system for helicopters
摘要
Abstract
Compared with numerous helicopter vibration reduction technologies,the top-mounted active control tech-nology on the rotor hub demonstrates significant advantages in volume,weight,and vibration suppression efficiency.Domestic research in this field remains in its early stages.A top-mounted active actuation system on the rotor hub was specifically designed to meet the actual operational requirements of a certain aircraft model.First,vibration reduction demands were determined in the rotating coordinate system.A mathematical model of the actuation unit output force was established,deriving the functional relationship between output force and motor control.An actuator configuration with automatic mass balancing functionality was designed.Second,to address the contradiction between the system's dynamic response rapidity and the voltage-current characteristics of the DC bus,an optimal position trajectory control strategy was proposed.The single-motor speed reference profile was planned as a quadratic function to reduce the inner-loop tracking difficulty.Leveraging the electrical braking energy flow characteristics,dual-motor position refer-ence profiles were optimized to achieve internal energy recovery and reduce voltage-current surges on the DC bus.Fi-nally,an engineering prototype was developed.Normalized experimental data show that the output force amplitude during actuation unit power loss is 0.11(per-unit value),with a maximum dynamic response time of 0.94.After implementing the dual-motor position optimization strategy,current surges decreased from 12.5 A to 8.3 A.These re-sults verify the feasibility and effectiveness of the system,providing practical guidance for the actual aircraft application of hub-mounted active actuation systems in China.关键词
桨毂顶置主动控制/桨毂顶置主动式作动器/位置轨迹/直升机/电源特性Key words
top-mounted active control on rotor hub/top-mounted active actuator for rotor hub/position trajectory/helicopter/power supply characteristics分类
航空航天引用本文复制引用
郝振洋,曹尚,张凤婷,侯兰兰..直升机桨毂顶置主动式作动系统设计[J].航空学报,2026,47(7):351-366,16.基金项目
国家自然科学基金(52077100) （52077100）
航空科学基金(201958052001) National Natural Science Foundation of China(52077100) （201958052001）
Aeronautical Science Foundation of China(201958052001) （201958052001）
