Approximate altitude transitions for high-speed aircraft
Approximate altitude transitions for high-speed aircraft
复制标题
高速飞机的近似高度转换
DOI：
10.2514/3.21423
复制
发表时间：
1995
影响因子：
2.6
通讯作者：
T. Whittaker
中科院分区：
文献类型：
--
作者：
M. Ardema;J. V. Bowels;E. J. Terjesen;T. Whittaker
在以前的文章中，一个高超声速，双模推进，升力飞行器从地球表面到地球轨道的上升轨道的近最优制导律被推导出来。能量状态近似被用来确定接近最佳的飞行路径和推进系统的操作。在本文中，瞬时的高度转换发生在能量状态近似的问题。该方法是模拟过渡作为一个序列的两个负载因子有界的路径（无论是爬升潜水或潜水爬升）。过渡的精确位置由与能态动力学模型相关的边界层方程的分析确定。
In a previous paper, a near-optimal guidance law for the ascent trajectory from Earth surface to Earth orbit of a hypersonic, dual-mode propulsion, lifting vehicle was derived. The energy-state approximation was used to determine the near-optimal flight path and the operation of the propulsion system. In this paper, the problem of the instantaneous altitude transitions that occur in energy-state approximation is addressed. The approach is to model the transitions as a sequence of two load factor-bounded paths (either climb-dive or dive-climb). The precise location of the transition is determined from analysis of the boundary-layer equations associated with the energy-state dynamic model.