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为了测定助推器分离时,作用于航天飞机固体助推器和轨道器/外贮箱上的气动力,做了一系列复杂的风洞试验。在这些试验中,用一种新颖而有效的方法处理了与使用三个相邻近的模型和模拟高压分离发动机羽流有关的问题。研究了一种新的数据处理方法,以便有效地处理那些作为许多自变量函数的数据。试验得到的数据可使气动特性误差的估算值大大减小,并且可以鉴定航天飞机分离系统在最大设计分离动压条件下的工作情况。飞行数据的整理还间接地验证了分离气动数据库及其有关误差。
A series of complex wind tunnel tests were conducted to determine the aerodynamic forces acting on the spacecraft solid booster and orbiter / outer tank when determining the booster separation. In these experiments, a novel and efficient approach to the problems associated with using three adjacent models and simulating the plume of a high-pressure split engine was used. A new approach to data processing has been studied to efficiently handle data that is a function of many independent variables. The experimental data can greatly reduce the estimation of the aerodynamic characteristic error and can identify the operation of the space shuttle separation system under the maximum designed dynamic separation pressure. The collation of flight data also indirectly verified the separation of aerodynamic database and its related errors.