This study proposes an equivalent dynamic environment design method based on a Chebyshev-Exact Dynamic Condensation framework for the efficient analysis of laminated composite spacecraft fuselage under thermo-mechanical coupling. The core innovation of this method lies in establishing a high-fidelity equivalent model that accurately accounts for the dynamic effects of the external shell. First, a unified dynamic equation for the coupled shell-plate fuselage system is formulated using artificial spring theory. Subsequently, the Chebyshev-Exact Dynamic Condensation framework is introduced: the spectral-Chebyshev method is employed for primary discretization and solution; the external shell is treated as a residual substructure, with its dynamic characteristics at the coupling interface with the inner plate preserved via Exact Dynamic Condensation; finally, the condensed dynamic matrix is applied as a virtual boundary to the target substructure, thereby establishing a high-fidelity equivalent dynamic environment model. Compared with traditional dynamic condensation methods, this framework strictly satisfies interface dynamic compatibility conditions, avoiding errors caused by degree-of-freedom truncation; In contrast to full-order finite element models, this framework significantly improves computational efficiency while maintaining comparable accuracy. Comparative validation confirms the generality, effectiveness, and accuracy of the proposed model under various boundary conditions. Based on this equivalent model, the influence mechanisms of target substructure parameters on the fuselage's dynamic response are further investigated, providing a new approach for the design and optimization of spacecraft structural dynamics.
Guo et al. (Wed,) studied this question.