This paper established the mathematical models of integral solid rocket ramjet, aerodynamics and trajectory, and wrote the corresponding C++ code.
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本文建立了固體火箭沖壓發(fā)動(dòng)機性能計算、導彈氣動(dòng)性能計算和彈道仿真分析等分系統的數學(xué)模型,并編制了相應的C++計算程序模塊。
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