Static State Simulation And Mass Optimization Of Space Orbital Transfer Vehicle Propulsion System

In this paper,the static state characteristic,system mass and mass optimization of the liquid propellant of Space Orbital Transfer Vehicle propulsion system were investigated.The static state mathematics model of the Space Orbital Transfer Vehicle propulsion system was established by the modularization way and the simulation software corresponding to the model was developed by LabVIEW.Then,the static simulation of four compound propulsion systems such as N₂O₄/MMH,N₂O₄/UDMH, LO₂/LH₂,LO₂/RP-1 were made separately.And the interfering factors analysis were made,the most sensitive interfering factors were found.The mass mathematics models of the main parts of the propulsion system, including tank,engine,pipe and valve,etc,were established by stress analysis.The static simulation results were imported and the mass model was solved.When the mass of propellant fixed or the work time fixed,the system mass and the total impulse of those above propulsion systems were calculated and the results were contrastively analyzed.The finite element analysis technique was applied to structure analysis and optimization design of the tank.For a specific tank in the space,the finite element model was established and the linear and nonlinear structure analysis was made.With the results of the analysis,optimization design and analysis of the flange and the wall thickness of tank were presented.Then,through comparing the results,the optimization model of the tank with less weight,better force status and suitable safe surplus was obtained.Based on the results of static state simulation,mass calculation and interfering factors analysis,considering the multiply interfering factors coupling effects, considering the thrust and impulse as the constrain conditions and the minimum system mass as the goal function,the optimization mass model was established.Programmed by LabVIEW,the mass optimization model was solved by Genetic Algorithms.The minimum mass value of the propulsion system and the parameters of design and performance of the system corresponding to the value were gotten.