| The Solid engine is the burning of solid rocket motor nozzle of indoor high temperature and high pressure gas exports.On the one hand,control the gas flow,to maintain the combustion chamber gas enough pressure;through the nozzle,on the other hand,the expansion speed,gas heat can be converted to the kinetic energy of gas flow,backward ejected at high speeds,counterproductive thrust.In an already set evaluation test flight,I unit made in one long tail appears on solid rocket motor nozzle blasting or burn through failure.Because of the nozzle is always influenced by high temperature,high pressure and high speed gas flow heat transfer and ablation.In order to completely find out the cause of the failure,and find out all potential failure factors,we carried out a lot of analysis to check work.This paper and the technical status of the same batch of long tail nozzle,process control,and by the test base has carried on the comprehensive quality of return products are review;Second ground fault repetition tests have been carried out,which makes fault signs got the repetition,then according to the appearance of fault recurrence,the theory of thermal structure analysis,engine flow calculation and long tail pipe cross section flow friction calculation,established the fault tree,analysis again ruled out after established the fault mechanism and reasons,finally based on the cause of the problem more e design of the product structure,puts forward the corresponding improvement measures.Finally by the status of process and the design structure and comprehensive analysis,improve and perfect,through multiple different test condition of the ground test and verify the effectiveness of the improvement measures,completely solve the end of a long tail nozzle blasting or burn through fault,improve the solid rocket launch pilot tail nozzle thermal structure design of the reliability. |
