Study On Interstage Scheme Of Solid Launch Vehicle Considering Residual Thrust

The solid carrier rocket is affected by the residual thrust force of the engine,and the interstage separation process is very complicated.In the history of China's aerospace engineering,rear-end accidents occurred because of insufficient estimation of residual thrust,causing heavy losses.Therefore,the problem of interstage separation under the effect of residual thrust of solid carrier rocket is deeply studied in this paper.The mathematical modeling of residual thrust,the collision reappearance in the traditional cold separation and the cold separation program improvement have been studied.Specific researches include:First,the one-dimensional isentropic flow algorithm is used to analyze the residual thrust of solid engine deeply,and the collision pheno mena in cold separation are reproduced.The generation mechanism of residual thrust after engine stage is analyzed,and the source and heat range involved during the residual thrust being produced by the solid engine are determined.The mechanism of gas generation in the heat insulation layer of the engine and the pyrolysis gas generation rate of the heat insulation layer in the process of ground test are analyzed.The pyrolysis gas production of the heat insulation layer in the post-effect stage is estimated according to the temperature range of the combustion chamber.Then,an interstage cold separation scheme suitable for solid carrier rocket is proposed.The cold interstage separation scheme is improved by considering the influence of residual thrust on interstage separation.Based on the cold separation scheme of split bolt + separation spring as power,aiming at a separation collision accident which is caused by not considering the effect of residual thrust in a solid rocket flying test,the improved de sign plan for the separation spring components is emphatically described,and the safety separation distance is analyzed after the improving design.The results show that no collision happens between the flight stage and the stage section,the stages depart is safe.Finally,the safety of the improved separation scheme is simulated and analyzed.From the aspects of gas flow,residual heat and arrow body structure,the influence of the improved design of the separation scheme is fully evaluated.The analysis results show that the gas flow after the ignition of the engine will not affect the flying of fight stage,and the engine ignition is safe under the condition of deviation.The correctness and effectiveness of the improved scheme are verified by the simulation.The smooth implementation of the project laid a solid foundation.