The application provides a multi-point approximation method based on an approximate Hessian matrix for structure optimization, comprising the following steps: step 1, establishing a finite
element model of a
spacecraft based on an initial design of a
spacecraft structure; step 2, performing mechanical prediction of the
spacecraft, and the analysis mode comprises
static analysis,
modal analysis, buckling analysis and
transient response; step 3, establishing a structure optimization
mathematical model, namely, defining an optimization target, a constraint function and a design variable; step 4, establishing a sequence approximation problem considering second-order information to approximate the original problem; step 5, estimating the Hessian matrix of the multi-point
approximation function by using a quasi-Newton method; step 6, selecting known points by using a neighborhood
selection strategy based on the
Euclidean distance; step 7, establishing convergence discrimination and an automatic
optimization system; step 8,
method comparison, analysis and iteration explicitness; and setting an optimization example to illustrate the flow from
spacecraft design to analysis and then to optimization, and the effectiveness is verified by comparing the results of the optimization method with those of a
commercial software.