本文利用一条等熵参考线和两个等焓偏导数建立了火箭发动机性能参数的外推公式。
In this paper, the extrapolation formulas of rocket engine performance parameters are established utilizing one isentropic reference line and two partial derivatives for fixed enthalpy.
同时，由于高动态环境下对数据更新率的要求，推导出轨道快速外推公式替代动力学方法来计算卫星的在轨位置。
At the same time, on the request to the data refresh rate in high dynamic environment, the paper deduces the rapid extrapolation algorithm of the orbit to replace dynamic model method.
导出了外推参数的计算公式。
The computing formulae for extrapolation parameters are also derived.
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