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本文推导了超音速导弹的气动特性与飞行性能参数两者之间的封闭解析式。气动特性系指诸如升力、零升阻力和诱导阻力.而飞行性能系指射程、速度、比射程、飞行路线角和机动载荷因子。低空导弹的长矩离巡航和滑翔用到这些关系式。对于爬升、巡航、滑翔、俯冲和攻击目标段均推导了相应的关系式。研究结果中包含了封闭式性能估算和指导外形设计的方程式。
In this paper, the closed analytical formulas of aerodynamic characteristics and flight performance parameters of supersonic missiles are deduced. Pneumatic characteristics are referred to as lift, zero lift resistance and induced resistance, and flight performance refers to range, speed, range, flight path angle and maneuver load factor. The long-range missiles use these relationships for cruising and gliding. The corresponding relationships are derived for the climb, cruise, glide, dive and target segments. The results of the study include equations for closed-form performance estimation and guidance profile design.