装药限燃包覆层脱粘和裂缝燃烧故障效应的试验研究

EXPERIMENTAL INVESTIGATION ON EFFECTS OF RESTRICT LAYER DEBONDING AND CRACK BURNING

关键词:  固体推进剂火箭发动机  绝热层  仿真试验  推进剂包覆  裂纹  失效模式

Key words:  Solid propellant rocket engine  Heat insulation layer  Simulation test  Propellant cladding  Crack  Failure mode

摘要:

用模拟试验研究各种脱粘和裂缝燃烧对发动机造成的故障效应，为故障诊断和失效分析提供依据。自由装填限燃包覆层装药的脱粘燃烧，造成燃面增大和由于压力升高造成的燃速指数增大效应；具有贴壁的限燃包覆层的装药脱粘燃烧，还会产生极其强烈的侵蚀燃烧效应。浅裂缝燃烧只是造成燃面增大的效应；而深裂缝装药燃烧，还会产生极其强烈的侵蚀燃烧效应。无论是贴壁的限燃包覆层的装药脱粘燃烧或是深裂缝装药燃烧，均会在发动机点燃的初期，产生十分强烈的压力峰，如果燃烧室的安全裕度不是特别大，则会在发动机点燃后的短暂时间内发生爆炸。

Abstract:

The fault effects on restrict layer debonding and crack burning were studied by simulated test in order to provide analysis basis of fault diagnostics for solid rocket engine.Test proved that the debonding of free load restrict layer resulted in increasing burning area and pressure exponent while the debonding of restrict layer pasted to chamber wall even resulted in effect of serious erosive burning.The debonding and the deep crack burning might cause serious pressure peak in the beginning of engine starting.If a strength margin was not big enough,a blast might happen in the very short period after ignition of the motor