Random vibration analysis for a flight device under multi-point strong correlated fluctuating pressures in the process of reentry into the atmosphere is studied. Starting from a free body modal analysis and considering strong correlation properties among fluctuating pressures, free body dynamic equations were established and random vibration theory under rigid-elastic modal coupling was deduced. The algorithm design is completed and the code is implemented in a self-developed parallel software platform PANDA. Correctness verification and application research were carried out with a typical numerical example. It shows that rigid body motion of the flight device has a significant impact on the response of structure in low frequency band, and it even plays a leading role. The closer to zero frequency, the greater the impact. In middle and high frequency bands, elastic response gradually takes dominant positions. A self-developed random vibration analysis module simulates well the dynamic response induced by fluctuating pressures in the flight device reentry process. It has a super large-scale parallel computing ability.

Based on self-developped parallel software platform PANDA, algorithm design and parallel implementation of multipoint-base-excited harmonic response were carried out via modal superposition method. Corresponding parallel solution module was constructed, rightness of which is validated by comparisons with commercial FE software. Parallel module was successfully applied to harmonic response analysis of SG facility. An effective parallel solution of extensive computing scale up to 1.188 billion DOFs was achieved. It shows that parallel solution module is suitable to large-scale refined harmonic response analysis of complex equipments, behaving a strong parallel computing scalability up to thousands of CPU processors, and going far beyond the scale of commercial FE software.