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能否用有限元模型精确地描述推进剂特性是工程师们研究航天飞机固体火箭发动机动力响应所关心的问题。通过试件试验确定的推进剂特性的不精确性使人们决定对航天飞机固体火箭发动机的独立段进行模态判定和模型相关。用多路输入法激励和确定惰性段及活性推进剂段的壳体/推进剂振型。这些试验在确定高阻尼的挠曲振型时非常成功,出现数对频率间隔小于2%的这种振型。应用这种先进的相关技术使人们能够在完成实验后两个星期内修正有限元模型使之和试验结果相一致,并且对精确地验证推进剂材料特性增加了置信度。
Whether the finite element model can accurately describe the propellant characteristics is an issue that engineers are concerned with studying the dynamic response of a space shuttle’s solid rocket motor. Inaccuracies in the characteristics of the propellants determined by the test specimens have led to the decision to model and model the independent segments of the space shuttle’s solid rocket motor. Enclosures / Propellant Modes for Encouraging and Determining Inert Sections and Active Propellant Segments Using Multiple Input Methods. These tests were very successful in determining the high-damping flexural modes with several pairs of modes with frequency separation less than 2%. The application of this advanced related technology enabled one to correct the FE model to the test results within two weeks of completing the experiment and increase the confidence in accurately verifying the propellant material properties.