固体推进剂火箭发动机用无损压痕技术评估老化复合推进剂的力学性能,Propellants, Explosives, Pyrotechnics

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固体推进剂火箭发动机用无损压痕技术评估老化复合推进剂的力学性能
Propellants, Explosives, Pyrotechnics ( IF 1.7 ) Pub Date : 2022-05-05 , DOI: 10.1002/prep.202100339
Bipin Kumar Bihari ₁ , Adepu Kumaraswamy ₂ , Mukesh Jain ₁ , Krothapalli P S Murthy ₁

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复合推进剂的老化研究是固体推进剂火箭发动机（SPRM）长期使用的重要方面之一。机械性能的评估对于在飞行试验前预测火箭发动机的结构性能至关重要。大多数情况下，复合推进剂老化行为的研究仅限于样品水平，无论是正常老化还是加速老化。在本研究中，尝试使用无损压痕技术评估 HTPB 基复合推进剂在全尺寸火箭发动机水平上的老化行为。采用万能试验机（UTM）和压痕技术对自然老化HTPB基复合推进剂样品的力学性能进行了综合研究。使用 UTM 和压痕数据之间的最小二乘法开发数学相关性。尝试建立用压痕技术直接评价复合推进剂老化行为的方法。建立的相关性在老化的复合推进剂样品上得到验证。此外，使用压痕技术评估了机龄 11 年的机龄 SPRM 推进剂的机械性能。

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Assessment of Mechanical Properties of Aged Composite Propellant Using Non-Destructive Indentation Technique in Solid Propellant Rocket Motor

Ageing study of composite propellant is one of the important aspects for the long term usage of a solid propellant rocket motor (SPRM). The assessment of mechanical properties is essential to predict the structural performance of rocket motors before its flight test. Mostly, the study of ageing behavior of composite propellant is limited to sample level which is subjected to either for normal ageing or accelerated ageing. In the present study, an attempt was made to assess the aging behavior of HTPB based composite propellant at full scale rocket motor level using a non-destructive indentation technique. The mechanical properties of naturally aged HTPB based composite propellant samples were comprehensively studied by both Universal Testing Machine (UTM) and indentation technique. The mathematical correlation was developed using least square method between UTM and indentation data. An attempt was made to establish the method to assess the aging behavior of composite propellant by indentation technique directly. The developed correlation was validated on aged composite propellant samples. Further, indentation technique was used to assess the mechanical properties of the propellant of in-flight fielded SPRM which was 11 years old.

更新日期：2022-05-05

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