摘要
民机高升力系统在飞机适航审定阶段,需要表明满足CCAR25.683条款要求。针对该条款,采用何种验证方法,是适航当局和飞机设计者普遍关注的问题。通过对CCAR25.683.条款的分析,提出了将实验室验证与分析/计算相结合的符合性验证方法。实验室验证在飞机地面模拟试验台上进行高升力系统操作试验验证,分析/计算通过对设计数据和静力试验机变形数据的计算,比较理论变形差值与实测补偿量;并提出了设计阶段考虑传动线系适应机翼变形的设计补偿思路,对高升力系统的试航验证及设计具有一定的参考价值。
Civil aircraft high lift system must be show compliance with CCAR25.683 during the certification phase.Airworthiness authority and manufacturer will discuss together and reach to appropriate method of compliance.Compliance verification method is provided,which combined the method of laboratory verification with analysis/calculation based on the analysis of CCAR25.683.Laboratory verification is based on verification of operation test of high lift system on the ground simulation test rig.Analysis/calculation method is based on the comparison of the theoretical deformation difference and measured compensation by calculating the design data and deformation data of static test machine.The design compensation method for accommodating wing bending during design phase is provided.The method is of some certain reference value for design and verification of high lift system.
出处
《航空工程进展》
2012年第1期125-130,共6页
Advances in Aeronautical Science and Engineering
关键词
高升力系统
适航验证
操作试验
机翼变形
high lift system
airworthiness certification
operation test
wing bending
