摘要
全机静力试验中,试验机悬空支持,通常采用六自由度静定约束,支持部位通常选择试验机上如起落架、发动机等刚度较大的非考核部位。考虑约束部位在试验过程中的变形,导致试验机姿态发生变化后试验加载误差增大,约束部位产生附加载荷或刚度。针对某通航小型飞机,提出了一种针对小型飞机全机静力试验的支持和约束方案,设计了起落架随动约束装置,并通过试验验证了该随动约束装置设计的合理性和可靠性,为类似小型飞机结构强度试验支持和约束装置设计提供了一种新的方法。
In the full scale aircraft static test,the tested aircraft is suspended for support,usually using six degrees of freedom statically determinate constraints,and the support parts are usually selected for non-assessment parts with large stiffness on the test aircraft,such as landing gear and engine.Considering the deformation of the restraint part during the test process,the test loading error increases after the posture of the test aircraft changes,and the constraint part generates additional load or stiffness.Aiming at a small general aviation aircraft,a support and restraint scheme for the full scale static test of the small aircraft is proposed,the landing gear follow-up restraint device is designed,and the rationality and reliability of the design of the follow-up restraint device are verified by experiments.It provides a new method for the design of structural strength test support and restraint devices similar to small aircraft.
作者
王彬
朱亚辉
Wang Bin;Zhu Yahui(Aviation Technology Key Laboratory of Full Scale Aircraft Structure Static and Fatigue Test,Aircraft Strength Research Institute of China,Xi′an 710065,Shaanxi,China)
出处
《工程与试验》
2023年第1期69-71,共3页
Engineering and Test
关键词
全机静力试验
静定约束
起落架
随动约束
full scale aircraft static test
statically determinate constraints
landing gear
follow-up restraint
