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Reliability Improvement of a Solid Rocket Motor in Early Design Phases

机译:早期设计阶段改进固体火箭发动机的可靠性

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Designing a reliable system is difficult and costly, due to the design process to be followed and test requirements. Itnis important to consider reliability in very early design phases, and it is essential to select a baseline design withnattainable high reliability. Therefore, in early phases, it is required to predict reliability and evaluate possiblenimprovements for the reliability of the design alternatives in a fast manner to make necessary design decisions. In thisnstudy, a solid rocket motor is considered as a case study, and it is aimed to determine important parameters that affectnthe solid rocket motor reliability, to assess ballistic performance and casing structural reliability, and to find a newndesign point to evaluate possible improvement range for its reliability. The variations in dimensions and materialnproperties, which are obtained from the previous data, are considered as the sources of failures and the limit states fornacceleration, and the total impulse and the maximum stress in the casing are approximated by the response surfacenmethod. Monte Carlo simulation is used with the response surface functions to assess the failure probability andndistributions of the rocket motor performance parameters. By considering the effect of the input parameters andndistribution functions of the performance parameters, a new design point is proposed to decrease the totalnprobability of failure.
机译:由于要遵循的设计过程和测试要求,因此设计可靠的系统既困难又昂贵。在非常早期的设计阶段就必须考虑可靠性,选择具有可持续性的高可靠性的基准设计至关重要。因此,在早期阶段,需要以快速的方式预测可靠性并评估设计方案可靠性的可能改进,以做出必要的设计决策。在本研究中,以固体火箭发动机为例进行研究,旨在确定影响固体火箭发动机可靠性的重要参数,评估弹道性能和机壳结构的可靠性,并找到新的设计点来评估可能的改进范围其可靠性。从以前的数据中获得的尺寸和材料特性的变化被认为是故障的来源和加速的极限状态,并且套管的总冲量和最大应力可以通过响应表面法来近似。蒙特卡罗模拟与响应面函数一起使用,以评估火箭发动机性能参数的失效概率和分布。通过考虑输入参数和性能参数的分布函数的影响,提出了降低故障总概率的新设计点。

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