Discussion on aeroelasticity of large aspect - ratio wing 基于结构优化的大展弦比机翼质量估算
Design method of active control law based on reduced order model of unsteady aerodynamics for aeroelasticity 基于非定常气动力低阶模型的气动弹性主动控制律设计
Using above methods to solve unsteady pressure distribution , coupling structure equations , the supersonic or hypersonic aeroelasticity is simulated in time - domain 运用上述的非定常气动力求解方法,耦合结构动力学方程,实现超音速、高超音速气动弹性的模拟。
Basing on the static aeroelasticity , the jig - shape and the attack angle design have been studied . generally , much computing time is needed in unsteady flow computation 利用现有条件自主开发出适合定常、非定常流场计算和气动弹性研究的分布式并行计算机系统。
At present , the equivalent plate methodology based on global ritz solution technique has been used in the studies of aeroelasticity and aeroelastic optimization of composite wing structures , but it stiff exits space to develop 鉴于此,常常采用连续的等效板模型( equivalentplatemodel ,简称epm ) 。目前,基于全局ritz求解技术的复合材料翼面结构等效板方法已用于气动弹性的基本研究和优化设计,但还不够成熟。
Aeroelasticity is the science which studies the interactions among inertial, elastic, and aerodynamic forces. It was defined by Arthur Roderick Collar in 1947 as "the study of the mutual interaction that takes place within the triangle of the inertial, elastic, and aerodynamic forces acting on structural members exposed to an airstream, and the influence of this study on design.