Optimization of Tactical Aircraft Maneuvers Utilizing High Angles of Attack
Optimization of Tactical Aircraft Maneuvers Utilizing High Angles of Attack
复制标题
利用大迎角的战术飞机机动优化
DOI：
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发表时间：
1982
期刊：
影响因子：
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通讯作者：
E. Berger
中科院分区：
文献类型：
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作者：
B. Well;E. Berger
未来的高性能飞机将具有高的推重比，将装备有控制构形飞行器技术，将是极轻的，并可能具有在“过失速”区域内以非常高的迎角飞行的能力。本文利用数值优化技术研究了过失速能力是否能改善几种战术机动的性能。具体地说，对于1）具有过失速能力的飞机A和2）不具有过失速能力但在其他方面与A相同的飞机B，计算了各种边界条件和飞行轨迹约束下的最短时间转弯机动。得出的结论是，对于两种组合的边界条件/路径约束，飞行时间可以减少，如果利用大迎角。然而，在大多数情况下，在载荷约束允许的情况下，在最大升力系数或接近最大升力系数时，作最短时间机动飞行。
Future high-performance aircraft will have high thrust/weight ratios, will be equipped with controlconfigured vehicle technology, will be extremely lightweight, and possibly have the capability of flying at very high angles of attack in the "poststall" region. This paper investigates, by using numerical optimization techniques, whether the poststall capability improves performance for several tactical maneuvers. Specifically, minimum-time turning maneuvers for a variety of boundary conditions and flight-path constraints are computed 1) for aircraft A which has poststall capability and 2) for aircraft B which does not, but is otherwise identical to A. It is concluded that for two combinations of boundary conditions/path constraints, flight time can be reduced if high angles of attack are utilized. In the majority of cases, however, minimum-time maneuvers are flown, load constraints permitting, at or near the maximum lift coefficient.