Flight Performance Modeling to optimize Trajectories
Flight Performance Modeling to optimize Trajectories
复制标题
飞行性能建模以优化轨迹
DOI：
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发表时间：
2016
期刊：
影响因子：
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通讯作者：
H. Fricke
中科院分区：
文献类型：
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作者：
J. Rosenow;H. Fricke
按照雄心勃勃的SESAR目标，新的飞机性能模型是必要的，以计算和优化考虑真实天气条件的自由航线飞机特定轨迹。在这里，提出了一种满足这些要求的飞机性能模型。为了考虑速度和加速度的恒定变化，对该非定常系统的动力学方程进行了解析求解。自由变量由飞机特定比例加积分加导数控制器控制。因此，该模型仅基于物理函数(除阻力极线外，该极线由Bada近似)，并且仅计算物理上可能的轨迹。包括几种飞机和发动机类型，可以对飞机的特定行为进行详细建模，并可以量化排放。以巡航高度和目标速度的变化为例进行了弹道优化。两者都是有效的变量。我们发现，所开发的优化目标函数不能推广到所有机型，特别是在真实天气条件下。单个飞机的特定目标函数主要取决于阻力极、最大马赫数和操作空重。
Along the ambitious SESAR objectives, new aircraft performance models are necessary to calculate and optimize free route aircraft specific trajectories considering real weather conditions. Here, an aircraft performance model is presented, which meets these requirements. To consider constant changes in speed and acceleration, the dynamic equation of this unsteady system is solved analytically. Free variables are controlled by an aircraft specific proportional plus integral plus derivative controller. Therewith, the model is based solely on physical functions (except for the drag polar, which is approximated by BADA) and calculates only physically possible trajectories. Several aircraft and engine types are included, the aircraft specific behavior can be modeled in detail and emissions can be quantified. Trajectory optimization is demonstrated by a variation of the cruising altitude and the target speed. Both are effective variables. We found, that the developed optimization target function cannot be generalized for all aircraft types, especially not under real weather conditions. Individual aircraft specific target functions mainly depend on the drag polar, the maximum Mach number and the operating empty weight.