Optimum climb and descent trajectories for airline missions
Optimum climb and descent trajectories for airline missions
复制标题
航空任务的最佳爬升和下降轨迹
DOI：
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发表时间：
1981
期刊：
影响因子：
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通讯作者：
H. Erzberger
中科院分区：
文献类型：
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作者：
H. Erzberger
应用最优控制理论，导出了结构受限于爬升段、稳定巡航段和下降段的最优定程弹道的特性。性能函数由燃料和时间成本之和组成，称为直接运行成本（DOC）。状态变量是行驶里程，自变量是能量。在该公式中，巡航段总是发生在足够大的范围的最佳巡航能量处。在短距离（400 N. mi.和更少），巡航段也可能出现在最佳巡航能量之下。这种巡航段的存在主要取决于燃料流量与推力特性的关系和推力约束。如果推力是一个自由控制变量沿着与空速，它表明，这样的巡航段一般不会出现。如果推力在爬升时被限制在某个最大值，而在下降时被限制在某个最小值，通常会出现这样的巡航段。
The characteristics of optimum fixed-range trajectories whose structure is constrained to climb, steady cruise, and descent segments are derived by application of optimal control theory. The performance function consists of the sum of fuel and time costs, referred to as direct operating cost (DOC). The state variable is range to go and the independent variable is energy. In this formulation a cruise segment always occurs at the optimum cruise energy for sufficiently large range. At short ranges (400 n. mi. and less), a cruise segment may also occur below the optimum cruise energy. The existence of such a cruise segment depends primarily on the fuel flow vs thrust characteristics and on thrust constraints. If thrust is a free control variable along with airspeed, it is shown that such cruise segments will not generally occur. If thrust is constrained to some maximum value in climb and to some minimum in descent, such cruise segments generally will occur.