Airframe structural optimization at different design stages results in new mass and stiffness distributions which modify the critical design loads envelop. Determination of aircraft critical loads is an extensive anal...Airframe structural optimization at different design stages results in new mass and stiffness distributions which modify the critical design loads envelop. Determination of aircraft critical loads is an extensive analysis procedure which involves simulating the aircraft at thousands of load cases as defmed in the certification requirements. It is computationally prohibitive to use a GFEM （Global Finite Element Model） for the load analysis, hence reduced order structural models are required which closely represent the dynamic characteristics of the GFEM. This paper presents the implementation of CMS （Component Mode Synthesis） method for the generation of high fidelity ROM （Reduced Order Model） of complex airframes. Here, sub-structuring technique is used to divide the complex higher order airframe dynamical system into a set of subsystems. Each subsystem is reduced to fewer degrees of freedom using matrix projection onto a carefully chosen reduced order basis subspace. The reduced structural matrices are assembled for all the subsystems through interface coupling and the dynamic response of the total system is solved. The CMS method is employed to develop the ROM of a Bombardier Aerospace business jet which is coupled with aerodynamic model for dynamic aeroelasticity loads analysis under gust turbulence. Another set of dynamic aeroelastic loads is also generated employing a stick model of same aircraft. Stick model is the reduced order modelling methodology commonly used in the aerospace industry based on stiffness generation by unitary loading application. The extracted aeroelastic loads from both models are compared against those generated employing the GFEM. Critical loads modal participation factors and modal characteristics of the different ROMs are investigated and compared against those of the GFEM. Results obtained show that the ROM generated using Craig Bampton CMS reduction process has a superior dynamic characteristics compared to the stick model.展开更多
Anti-plane punch-through shear test and anti-planefour-point bending test are used to study the crack initiation and propagation under anti-plane shear (Mode Ⅲ) loading. The tensile and shear stresses at the crack ti...Anti-plane punch-through shear test and anti-planefour-point bending test are used to study the crack initiation and propagation under anti-plane shear (Mode Ⅲ) loading. The tensile and shear stresses at the crack tip are calculated by finite element method. The results show that under Mode Ⅲ loading the maximum principal stress σ1 at crack tip is smaller or a little larger than the maximum shear stress τmax. Since the tensile strength of brittle rock is much lower than its shear strength, σ1 is easy to reach its critical value before τmax reaches its critical value and thus results in Mode I fracture. The fracture trajectory is helicoid and the normal direction of tangential plane with the fractured helicoid is along the predicted direction of the maximum principal stress at the notch tip. It is further proved that Mode Ⅰ instead of Mode Ⅲ fracture occurs in brittle rock under Mode Ⅲ loading. The fracture mode depending on the fracture mechanism must be distinguished from the loading form.展开更多
稀疏主成分分析是一种用于降维和特征选择的无监督方法。由于计算多个主成分时主载荷向量间不具有相同的稀疏模式,导致难以从原始特征空间中确定出对主成分贡献最大的小部分变量,为解决此问题,提出一种自适应稀疏主成分分析(Adaptive sp...稀疏主成分分析是一种用于降维和特征选择的无监督方法。由于计算多个主成分时主载荷向量间不具有相同的稀疏模式,导致难以从原始特征空间中确定出对主成分贡献最大的小部分变量,为解决此问题,提出一种自适应稀疏主成分分析(Adaptive sparse principal component analysis,ASPCA)算法。首先使用组套索模型,通过在载荷向量上施加块稀疏约束得出自适应稀疏主成分分析公式,随后对稀疏矩阵的不同列使用不同的调整参数获得自适应惩罚,最后运用块坐标下降法对自适应稀疏主成分分析公式进行两阶段优化,从而找到稀疏载荷矩阵和正交矩阵,实现降维的最优化。对稀疏主成分分析(Sparse principal component analysis,SPCA)算法、结构化且稀疏的主成分分析(Structured and sparse principal component analysis,SSPCA)算法和ASPCA算法进行仿真比较,结果表明ASPCA算法的降维性能更优,能提取更有价值的特征,从而显著提高了分类模型的平均分类准确率。展开更多
文摘Airframe structural optimization at different design stages results in new mass and stiffness distributions which modify the critical design loads envelop. Determination of aircraft critical loads is an extensive analysis procedure which involves simulating the aircraft at thousands of load cases as defmed in the certification requirements. It is computationally prohibitive to use a GFEM （Global Finite Element Model） for the load analysis, hence reduced order structural models are required which closely represent the dynamic characteristics of the GFEM. This paper presents the implementation of CMS （Component Mode Synthesis） method for the generation of high fidelity ROM （Reduced Order Model） of complex airframes. Here, sub-structuring technique is used to divide the complex higher order airframe dynamical system into a set of subsystems. Each subsystem is reduced to fewer degrees of freedom using matrix projection onto a carefully chosen reduced order basis subspace. The reduced structural matrices are assembled for all the subsystems through interface coupling and the dynamic response of the total system is solved. The CMS method is employed to develop the ROM of a Bombardier Aerospace business jet which is coupled with aerodynamic model for dynamic aeroelasticity loads analysis under gust turbulence. Another set of dynamic aeroelastic loads is also generated employing a stick model of same aircraft. Stick model is the reduced order modelling methodology commonly used in the aerospace industry based on stiffness generation by unitary loading application. The extracted aeroelastic loads from both models are compared against those generated employing the GFEM. Critical loads modal participation factors and modal characteristics of the different ROMs are investigated and compared against those of the GFEM. Results obtained show that the ROM generated using Craig Bampton CMS reduction process has a superior dynamic characteristics compared to the stick model.
基金Project (50374073)supported by the National Natural Science Foundation of China project (2002032256)supported bythe Postdoctor Science Foundation of China
文摘Anti-plane punch-through shear test and anti-planefour-point bending test are used to study the crack initiation and propagation under anti-plane shear (Mode Ⅲ) loading. The tensile and shear stresses at the crack tip are calculated by finite element method. The results show that under Mode Ⅲ loading the maximum principal stress σ1 at crack tip is smaller or a little larger than the maximum shear stress τmax. Since the tensile strength of brittle rock is much lower than its shear strength, σ1 is easy to reach its critical value before τmax reaches its critical value and thus results in Mode I fracture. The fracture trajectory is helicoid and the normal direction of tangential plane with the fractured helicoid is along the predicted direction of the maximum principal stress at the notch tip. It is further proved that Mode Ⅰ instead of Mode Ⅲ fracture occurs in brittle rock under Mode Ⅲ loading. The fracture mode depending on the fracture mechanism must be distinguished from the loading form.
文摘稀疏主成分分析是一种用于降维和特征选择的无监督方法。由于计算多个主成分时主载荷向量间不具有相同的稀疏模式,导致难以从原始特征空间中确定出对主成分贡献最大的小部分变量,为解决此问题,提出一种自适应稀疏主成分分析(Adaptive sparse principal component analysis,ASPCA)算法。首先使用组套索模型,通过在载荷向量上施加块稀疏约束得出自适应稀疏主成分分析公式,随后对稀疏矩阵的不同列使用不同的调整参数获得自适应惩罚,最后运用块坐标下降法对自适应稀疏主成分分析公式进行两阶段优化,从而找到稀疏载荷矩阵和正交矩阵,实现降维的最优化。对稀疏主成分分析(Sparse principal component analysis,SPCA)算法、结构化且稀疏的主成分分析(Structured and sparse principal component analysis,SSPCA)算法和ASPCA算法进行仿真比较,结果表明ASPCA算法的降维性能更优,能提取更有价值的特征,从而显著提高了分类模型的平均分类准确率。
