| 倾转四旋翼飞行器直升机模式操纵策略研究 |
| |
| 引用本文： | 周攀,陈仁良,俞志明.倾转四旋翼飞行器直升机模式操纵策略研究[J].航空动力学报,2021,36(10):2036-2051. |
| |
| 作者姓名： | 周攀 陈仁良 俞志明 |
| |
| 作者单位： | 南京航空航天大学 航空学院 直升机旋翼动力学国家级重点实验室，南京 210016 |
| |
| 基金项目： | 国家自然科学基金（11672128）； 江苏高校优势学科建设工程资助项目 |
| |
| 摘 要： | 由于倾转四旋翼飞行器具有特殊的构型，针对直升机模式下的操纵策略，建立了样机的非线性飞行动力学模型并结合试验数据进行了验证，提出了适用于直升机模式的四种操纵方式，对比了不同操纵方式相应的配平值、操纵功效及操纵耦合，随后确定了一组相对合理的操纵方式，解决了倾转四旋翼飞行器在直升机模式下操纵冗余的问题。分析了重心位置对所确定操纵方式的配平特性和操纵功效的影响。结果表明:纵横向通道下总距差动引起的操纵功效比周期变距联动大得多；偏航通道下周期变距差动引起的操纵功效大于总距差动，横向周期变距差动引起的交叉耦合小于纵向周期变距差动；正常重心位置所得到的配平量和交叉耦合最小。
|
| 关 键 词： | 倾转四旋翼飞行器 飞行动力学模型 配平 操纵策略 操纵功效 操纵冗余 |
| 收稿时间： | 2020/9/13 0:00:00 |
Investigation of control strategy for quad-tilt-rotor aircraft in helicopter mode |
| |
| ZHOU Pan,CHEN Renliang,YU Zhiming.Investigation of control strategy for quad-tilt-rotor aircraft in helicopter mode[J].Journal of Aerospace Power,2021,36(10):2036-2051. |
| |
| Authors: | ZHOU Pan CHEN Renliang YU Zhiming |
| |
| Affiliation: | National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China |
| |
| Abstract: | Quad-tilt-rotor aircraft is a vehicle of particular configuration.For its strategy of the helicopter mode，a nonlinear flight dynamic model was established for a prototype，and some relevant test were carried out.Four control strategies were proposed，and a relatively reasonable control strategy was determined by comparing the trim values，control efficiency and cross coupling.The control redundant problem of quad-tilt-rotor aircraft in helicopter mode was solved under the strategy.At last，the influence of the center of gravity location on trim characteristics and control efficiency was analyzed.The results showed that the main control efficiency of longitudinal and lateral channel obtained by collective differential was much greater than by linkage of cyclic pitch.The main control efficiency of yaw channel obtained by cyclic pitch differential was greater than by collective differential.The cross coupling of yaw channel obtained by lateral cyclic pitch differential was less than longitudinal cyclic pitch differential.The values of trimming and cross coupling were the minimum at the normal position of center of gravity. |
| |
| Keywords: | quad-tilt-rotor aircraft flight dynamic model trim control strategy control efficiency control redundant |
|
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
|
点击此处可从《航空动力学报》下载全文 |
