Separation Process Simulation Based On Multiple Factors And Identification Research For Devistion

The spacecraft separation dynamic simulation is usually for a specific separationplan at this stage. Yet there is no versatility separation simulation software. In this paper,we design the general separation of simulation software and identify the deviations inthe separation process.In this paper，the dynamic simulation of two-body system is the emphasis. Thisresearch has made the mathematical models and simulated for the typical separationsystems. Take the full account of the separation of body posture changes in theseparation process; consider the deviation of the general, pneumatic, power and otherfactors which brought uncertain influence. Simulate the vehicle’s separation process. Itcan be better and more truly to indicate the correctness of the separation design, and canprecise verify the timing of the separation, the separatist movement process and eventhe separation programs.In this thesis, a method which can calculate and analyze a variety of space launchvehicle separation movement of the two-body types is proposed for the design andrealization of two-body simulation software. Add the outer loads according to the user’schoice. It has the characteristics of wide range of applications and strong flexibility.Input the motion states of the combination, the mass characteristics of the separationbodies and outer load changes. Using integral calculation a trajectory curves can be get.The function can demonstrate the correctness of the software. The simulation time, theintegration step, output step size and separation of specific points can be set. Thefourth-order Runge-Kutta method and fourth-order Adams forecast correction methodhas been used for solving first order differential equations.The software also has the function of inferring the outer load changes based on themovement curves. In actual test, the obtained results may be very little, and the possibledeviation may be large. We use the uniform experimental method to design deviationcombinations and seek the optimal combination of the deviation for the separationprogram designers.This thesis simulate and analyze the separation process of the monomer fairing andthe stages, considering the aerodynamic, the separation rocket thrust, the main stagerocket thrust and other factors. Get and analyze the movement regularity of the fairingand the rocket after been calculated.