在研究气动弹性力学和受控结构动力学问题进行稳定性或响应分析时,一般需要求解下列复矩阵的非线性参数特征值问题A(C,λ)q=0(1a)p~τA(C,λ)=0(1b)式中A为n×n复矩阵,其元素是标量C和λ在某区域内的可导的代数函数或超越函数,通常 In the study of stability or response analysis of aeroelasticity and controlled structural dynamics problems, it is generally necessary to solve the following eigenvalue problem for nonlinear parameters of the complex matrix A (C, λ) q = 0 (1a) p ~ τA (C , λ) = 0 (1b) where A is an n × n complex matrix whose elements are derivable algebraic functions or transcendental functions of scalar C and λ in a region, usually