舵面直接力矩加载系统设计与仿真  

Design of Direct Torque Loading System on Control Surface

作　　者：韩龙柱[1] 邓晴莺 王宝奇 刘棣斐[3] 裴忠才[3] 

机构地区：[1]北京航空航天大学生物与医学工程学院,100191 [2]北京魔诘创新科技股份有限公司,100029 [3]北京航空航天大学自动化学院,100191

出　　处：《系统仿真学报》2013年第S1期212-215,共4页Journal of System Simulation

摘　　要：飞行器舵面力矩模拟加载对整个飞行器的设计和定型有着重要意义。传统力矩加载方式多为轴对顶方式,应用场合受到较大限制。在吸取轴对顶加载方式经验的基础上,设计出一种利用铝型材搭建的专用翼面加载支架以实现飞行器的整机直接加载,具有快速装卸,轻便坚固的特点。在力矩加载过程中,舵机运动会对力矩指令的模拟跟踪造成额外影响,即产生了多余力矩。针对飞行器舵面加载的这种典型被动式特征,采用基于自测速形式的结构不变性原理方法抑制舵机自主运动过程中产生的多余力矩,并最终通过仿真和实物验证实现整个力矩加载系统的设计。Torque loading simulation aircraft control surface plays an important role in the procedure of aircraft design.Traditionally,the torque is loaded on the actuator axis,which is always restricted by the application conditions.On the basis of traditional methods,a new implement with aluminum profile structure was designed to load the torque directly on the control surface.The original structure is light,solid as well as convenient in handling.A structure unchangeable principle method based on measuring itself velocity was implied to restrain the disturbance torque.Finally,the system was designed according to simulation and experiments.

关 键 词：力矩模拟 直接加载 被动式加载 结构不变性原理 多余力抑制 

分 类 号：V227[航空宇航科学与技术—飞行器设计]