【作者】 耿建中； 段卓毅； 赵彦； 王钟毓；

【Author】 Geng Jianzhong;Duan Zhuoyi;Zhao Yan;Wang Zhongyu;AVIC The First Aircraft Institute;

【机构】 航空工业第一飞机设计研究院；

【摘要】 现行公开资料和飞机设计品质规范中,没有给出飞机纵向杆力特性的具体设计方法,本文分析了杆力特性的静态特性,研究了理想设计与实际特性之间的差异;通过对操纵载荷系统动态特性的研究,建立了二阶系统模型,根据驾驶员对杆力系统动态特性要求,初步确定杆力特性主要参数可接受的变化范围;研究了飞机品质规范对大型飞机不同情况下的操纵力要求,给出了满足操纵要求的杆力特性参数可接受的范围;综合杆力系统动态特性和品质规范要求,确定了某大型飞机纵向操纵杆力特性,并通过线性度量化指标进行了线性度度量。由结果可知,对于某一气动特性确定的飞机,设计满足所有要求的杆力特性可能很难实现,无法保证所有指标要求时,可采用控制系统辅助实现。更多还原

【Abstract】 The design method of aircraft longitudinal stick force characteristics is not given in present published materials and flight quality certification.The static characteristics of stick forcr characteristics was analyzed in paper,and the difference of ideal design and practical design performance was studied;the second order system models were established based on dynamic performance of control load system,according the requirements of dynamical characteristics of stick force system,the acceptance scope of main parameters of stick force characteristics was determined primarily;the control force command for different situations of large aircraft,the acceptance scope of stick force characteristics parameters which satisfy operate requirement was given;the longitudinal stick force characteristics was determined combined the stick force system dynamical performance with flight quality certifications.Meanwhile,the linear measurement index was used in measuring.According to results,for one aircraft whose aerodynamic performance is given,it is not possible for all index to satisfy stick force characteristics,in this condition,the aided control system can accomplished.更多还原