Modeling and simulation framework for missile launch dynamics in a rigid-flexible multibody system with slider-guide clearance

This paper proposes a novel framework for missile launch dynamics modeling and simulation, with a focus on ground-based missile launching vehicles. Our model treats the launching vehicle as a hybrid rigid-flexible multibody system, capturing spatial vibrations with the launch canister modeled as a flexible beam and other as rigid bodies, applying the linear multibody system transfer matrix method. The equations of motion of the rigid missile, with respect to the launch canister, are derived through the Newton-Euler method. The missile is equipped with sliders that interact with the guide inside the launch canister, ensuring stability and adherence to a predefined trajectory during launch. Crucially, our framework also accounts for the clearance between the slider and guide, a factor often overlooked in existing models. When the slider contacts the guide, an impact occurs, and its dynamic response is modeled by the contact impact force, which is considered an external force on the system. Acknowledging the bending characteristics of the launch canister, we propose a mathematical model for detecting contact between the slider and guide and calculating their relative position and velocity. Subsequently, we formulate coupled equations of motion for the launching vehicle and missile. Validation of our framework was conducted using experiments with simplified launch vehicle models and commercial software simulations, confirming its applicability. The simulation parameters for the comprehensive launching vehicle model are ascertained through modal testing and parameter identification. Our analysis reveals that slider-guide clearance and the introduction of an additional slider pair significantly influence missile stability and angular variation during launch dynamics.