| 轻型飞机副翼操纵系统中改进的RSSR机构研究 |
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| 引用本文： | 谢习华,陈志伟,欧阳星,王小飞,王晓玲.轻型飞机副翼操纵系统中改进的RSSR机构研究[J].航空工程进展,2017,8(2):213-218. |
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| 作者姓名： | 谢习华 陈志伟 欧阳星 王小飞 王晓玲 |
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| 作者单位： | 1. 中南大学高性能复杂制造国家重点实验室,长沙410083;山河智能装备股份有限公司技术中心,长沙410100;2. 中南大学高性能复杂制造国家重点实验室,长沙,410083;3. 山河智能装备股份有限公司技术中心,长沙,410100 |
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| 基金项目： | 湖南省科技计划项目（2016wk2032） |
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| 摘 要： | 精确控制副翼偏转角度对提高轻型飞机的操纵性能具有重要意义,将改进的空间四连杆机构——RSSR应用于轻型飞机副翼操纵系统的传动末端,采用方向余弦矩阵法建立RSSR机构运动的数学模型,并推导出该机构的位移方程,在ADAMS软件中对该机构进行参数化建模,确定目标函数、约束函数和驱动函数;优化算法选用广义简约梯度算法,对敏感程度较高的设计变量进行优化设计。结果表明:RSSR机构中各点的相对位置对副翼偏转角度影响较大,副翼上下偏转角度的相对误差分别从初始的2.35%与5%降低为0.100 5%与0.103 3%,采用RSSR机构可有效提高对飞机副翼偏转角度的控制精度。研究成果最终应用于某五座复合材料轻型飞机样机中。
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| 关 键 词： | 轻型飞机 副翼操纵系统 RSSR ADAMS 优化设计 |
| 收稿时间： | 2017/1/24 0:00:00 |
| 修稿时间： | 2017/2/25 0:00:00 |
Research on RSSR mechanism of Light Aircraft Aileron Control System |
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| Xie Xihu,Chen Zhiwei,Ouyang Xing,Wang Xiaofei and Wang Xiaoling.Research on RSSR mechanism of Light Aircraft Aileron Control System[J].Advances in Aeronautical Science and Engineering,2017,8(2):213-218. |
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| Authors: | Xie Xihu Chen Zhiwei Ouyang Xing Wang Xiaofei and Wang Xiaoling |
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| Affiliation: | Key State Laboratory of High Performance Complex Manufacturing,College of Mechanical and Electrical Engineering,Central South University,Key State Laboratory of High Performance Complex Manufacturing,College of Mechanical and Electrical Engineering,Central South University,Sunward Intelligent Equipment Co,Ltd,Key State Laboratory of High Performance Complex Manufacturing,College of Mechanical and Electrical Engineering,Central South University,Key State Laboratory of High Performance Complex Manufacturing,College of Mechanical and Electrical Engineering,Central South University |
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| Abstract: | In order to make the angles of aircraft aileron deflection can be controlled more accurately, an improved spatial four-bar (RSSR) mechanism is applied to the end of the transmission mechanism of the light aircraft aileron control system. The mathematical model of the mechanism is established by the method of direction cosine matrix, and the displacement formula of the mechanism is derived. In order to make an optimization design of RSSR mechanism, the parametric model of the mechanism is established in the software of ADAMS by estimating the initial value of the mechanism parameters, the objective function, the constraint function and the deriving function are determined, the sensitivity of each design point to the objective function was studied, the optimal design of the design variables with high sensitivity is carried out by the generalized reduced gradient algorithm. The results show that the aileron deflection angle has great influence by the relative position of each point of the RSSR mechanism, the relative error of the deflection angle of the aileron upward and downward are reduced from the initial 2.35% and 5% to 0.1005% and 0.1033% respectively, which demonstrated the optimization design for the mechanism meet the requirements of precision exactly. For the purpose of verifying the feasibility of the mechanism, the three-dimensional modeling for the mechanism is established in the software of CATIA, and used in a prototype of a 5-seat composite material light aircraft finally. |
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| Keywords: | light aircraft aileron control system RSSR ADAMS optimization design |
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