Research And Application Of A Particular Model Class Separation

Separation process problem for a missile are studied in this paper. In addition, some helpful conclusions that can assist solving practical project problems .In the study, some feasible separation methods are compared and analyzed. Then, theconnected flying, stage separation is simulated in computer, theinfluences imposed by working conditions and interfering factors for separation process areanalyzed. Furthermore, if the missile is controlled non-rolling, the stage separation process issimulated in another model. Some of conclusions derived from above analysis are checked intheory. Finally, the finite element software ANSYS is used to analyze the stress of missileconnecting mechanism in critical moments, which displays the inner load changes with the outerforce.Based on the features comparison of some separation methods, a suitable separation method and separation mechanism is chosen. According to flight dynamics, a particle model and an attitude model in launching coordinate system and in quasi missile body coordinate system are established, the influence imposed by constant wind, thrust bias of the motor and connection bias are analyzed. And still deflection separation model when the missile is controlled non-rolling are built, separation process are digitally simulated to check the stability during it. In order to validate above models, some formulas derived from dynamics theories are deduced; models are proved reasonable and conclusions are in accord with experience. In the end, the structure strength of missile connecting mechanism is analyzed by the finite element software ANSYS which proves its design successful.It is of great importance for missile separation process , and is valuable for the simulation of other missiles' stage separation process on the study in this paper.