用奇异扰动分析法确定了一种吸气式导弹的最优射程—燃油—时间弹道。这种方法构建了降阶“巡航—冲刺”模型。由于动力学系统包含过去未曾使用过的限制条件拓宽了这一领域的早期研究。早期研究结果表明在导弹能够飞行的整个速度范围内。由于在某些情况下工作点急剧变化,在很高和很低速度状态的使用范围大大缩小了。同时,也相当详细地研究了非零最小允许节流位置和所产生的节流自激振动对该控制问题解的影响。也研究了能量的瞬变过程。 A singular perturbation analysis method is used to determine the optimal range of an aspirated missile - the fuel-time trajectory. This method builds a reduced-order “cruise-sprint” model. Early studies in this area have been broadened by the inclusion of kinematic systems with constraints not previously used. Earlier studies showed that the entire speed range in which missiles can fly. Due to drastic changes in operating points in some cases, the use of very high and very low speeds has been greatly reduced. At the same time, the effect of non-zero minimum allowable throttling position and resulting throttling self-excited vibration on the solution of this control problem is also studied in considerable detail. The energy transients are also studied.