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.

To enforce accurate displacement constraints,essential boundary conditions and interface continuity conditions in mesh-less method are treated as Multi-Point Constraints (MPC) of displacement,which are illustrated by using SPH (Smoothed Particle Hydrodynamics) method incorporated with algebraic master-slave relations.An example of linear elastic problem of representative volume element in matrix-inclusion composite is presented.Numerical tests show that the proposed algebraic master-slave method leads to higher accuracy and wider application than the penalty function method.