Based on the modern control theory, an aerofoil finite element control model is established by using MSC Nastran DMAP (Direct Matrix Abstraction Program). The vibration control is studied with linear quadratic optimal control theory proposed.
英
美
- 利用MSCNastran開(kāi)發(fā)語(yǔ)言DMAP(DirectMatrixAbstractionProgram)；基于現代控制理論；建立機翼有限元結構的振動(dòng)控制模型；并使用線(xiàn)性二次型最優(yōu)控制理論對機翼結構進(jìn)行振動(dòng)抑制研究.
