民用飞机尾翼及后机身考虑非线性效应的变形干涉研究  

Deformation interference of civil aircraft tail fin and rear fuselage considering nonlinear effects

作　　者：陈率[1] Chen Shuai(Shanghai Aircraft Design and Research Institute,Shanghai,201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《机械设计与制造工程》2023年第5期59-63,共5页Machine Design and Manufacturing Engineering

摘　　要：中国民用航空规章第25部《运输类飞机适航标准》§25.655条款(a)要求:可动尾面的安装必须使得当某一尾面处在极限位置而其余各尾面作全角度范围的运动时,任何尾面之间没有干扰。民用飞机尾翼翼面、舵面有限元内力分析是进行尾翼结构设计和强度校核的基础。以某型号的低平尾结构模型为例,对模型坐标系旋转变换、返力连杆作动器非线性效应、对应模型载荷处理进行了研究,从而使水平安定面与升降舵、垂直安定面与方向舵、平尾与后机身、垂尾与后机身间的各场景的变形分析完整、准确,理论计算值与试验监测值基本一致,结构间并未发生干涉,符合§25.655条款(a)要求。China Transport Aircraft Airworthiness Standard 25.655 Installation(a)state:The movable tail surfaces must be installed properly so that there is no interference between any tail surfaces when one of the tail surfaces is in the limit position and the other tail surfaces are moving in a full angular range.The finite element analysis of the internal forces in the tail surfaces and rudder surfaces of civil aircraft is the basis for its structural design and strength checks.The analysis results directly affect the strength assessment conclusions,thereby affect the structural design.It focuses on the transformation of the model coordinate system,the nonlinear effect of the force feedback linkage actuator,and the model load handling,so that the deformation scene analysis between the horizontal stabilizer and the elevator,the vertical stabilizer and the rudder,the horizontal tail and the rear fuselage is more complete and accurate.The validation results are in accordance with 25.655 Installation(a).

关 键 词：变形内力计算 作动器位置 坐标系变换 尾翼载荷处理 

分 类 号：TP3[自动化与计算机技术—计算机科学与技术]