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为分析某航天型号镁铝贫氧推进剂失效机理,利用显微形貌分析、X射线衍射(XRD)、热分析和高速摄影等测试了贫氧推进剂的成分、热分解规律以及常压点火性能。结果表明,吸湿后推进剂中的高氯酸铵(AP)发生结块,Mg被氧化后与水作用生成Mg(OH)_2。未吸湿的推进剂在420℃前仅有AP的晶型转变及热分解失重,而吸湿后推进剂热稳定性变差,90℃下即开始失重,420℃前有四个分解步骤:水分挥发、Mg(ClO_4)_2热分解及AP与Mg(OH)_2分解。采用电点火头在常压下点燃后,未吸湿推进剂可以稳定燃烧,而吸湿后的推进剂无法被引燃。分析认为,导致推进剂点火失效的原因是AP结块和活性镁含量降低,因此镁铝贫氧推进剂在潮湿环境下的贮存应给予重点关注和定期抽样监测。
In order to analyze the failure mechanism of magnesium-aluminum-poor oxygen propellant for a spaceflight model, the composition and thermal decomposition of oxygen-poor propellants were investigated by means of micro-morphology, X-ray diffraction (XRD), thermal analysis and high-speed photography. performance. The results showed that ammonium perchlorate (AP) was agglomerated in the propellant after moisture absorption, and Mg was oxidized to form Mg (OH) 2 with water. The non-hygroscopic propellant had only the crystalline transition and thermal decomposition weight loss of AP before 420 ℃, but the thermal stability of the propellant after hygroscopic became worse. The weight loss began at 90 ℃. There were four decomposition steps before 420 ℃: water volatilization , Thermal decomposition of Mg (ClO_4) _2 and decomposition of AP and Mg (OH) _2. After using electric ignition head lit at atmospheric pressure, the non-hygroscopic propellant can stabilize combustion, and the moisture-absorbed propellant can not be ignited. Analysis suggests that the cause of ignition failure of propellant is due to the reduction of AP agglomeration and active magnesium content. Therefore, the storage of magnesium-aluminum oxygen-poor propellant in humid environment should be given the key attention and regular sampling monitoring.