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本文讨论的一种方法,能用来估算研制航天飞机轨道器时所用的气动加热设计法和防热系统热性能计算法中的不确定度。该方法被用来预测轨道器再入过程中防热系统预期热响应或额定热响应,周围的不确定度带。首先,确定了对这种不确定度带起重要影响的流场参数和防热系统参数,然后用统计方法把这些参数合并,使之在一定程度上适合于进行工程估算,从而算出防热系统的热置信区间和以设计温度极限为基准的温度裕度。对某个选定的防热系统设计来说,可以用这个方法来拟定轨道器未来飞行工况的再入飞行轨迹,使之既能满足温度裕度的要求,又能满足热置信区间的要求。本文对现有的轨道器防热系统设计中选出的一些区域,针对早期飞行试验工况中具有代表性的再入飞行轨迹,进行了热设计裕度的评定,用这样的实例阐明了本方法。
One of the methods discussed in this paper can be used to estimate the uncertainty in the aerodynamic heating design method and the thermal performance calculation method used in the development of a space shuttle orbiter. This method is used to predict the expected thermal response or thermal response of the thermal protection system during orbit reentry with the surrounding uncertainty band. First, the parameters of the flow field and the thermal protection system, which have an important influence on this uncertainty, are determined. These parameters are then statistically combined to make them suitable to carry out engineering estimates to a certain degree to calculate the thermal protection system Of the thermal confidence interval and the design temperature limit as a benchmark temperature margin. For a given design of thermal protection system, this method can be used to formulate the reentry flight trajectory of the future orbit of the orbiter so as to satisfy both the temperature margin requirement and the thermal confidence interval requirement . In this paper, some areas selected in the design of the existing orbiter heat-protection system are designed to assess the margin of thermal design for the representative re-entry flight path in early flight test conditions. method.