Active-Control System for Breakup of Airplane Trailing Vortices
Active-Control System for Breakup of Airplane Trailing Vortices
复制标题
打破飞机尾涡的主动控制系统
DOI：
10.2514/2.1244
复制
发表时间：
2001
期刊：
影响因子：
2.5
通讯作者：
P. Spalart
中科院分区：
文献类型：
--
作者：
J. Crouch;G. Miller;P. Spalart
机翼操纵面用于触发襟翼放下布局中飞机后面的尾涡破裂。在飞机的近场有多对涡，这承认新的不稳定性机制，不存在于一个单一的涡对。控制面的周期性运动用于引入一种独特形式的扰动，这种扰动在多涡对系统中被放大，但保持了总环量、升力和滚转力矩。扰动的增长导致右舷和左舷涡周期性地收缩成一系列涡环。通过数值模拟和拖曳水池实验验证了这一概念。结果表明，该系统打破了尾随涡更迅速地比一个可比的激励Crow不稳定性的一对涡。该系统的总体效能取决于飞机的构型，即襟翼系统和平尾的细节
Wing control surfaces are used to trigger the breakup of trailing vortices behind aircraft in a flaps-down configuration. In the near field of the aircraft there are multiple pairs of vortices, which admit new instability mechanisms that do not exist on a single pair of vortices. A periodic motion of the control surfaces is used to introduce a unique form of perturbation that is amplified in the multiple vortex-pair system but conserves total circulation, lift, and rolling moment. Growth of the perturbations leads to the periodic pinching of the starboard and port vortices into a series of vortex rings. The concept is demonstrated using numerical simulations and towing-tank experiments. Results show that the system breaks up the trailing vortices more rapidly than a comparable excitation of the Crow instability on a single pair of vortices. The overall effectiveness of the system depends on the airplane configuration, namely, details of the flap system and the horizontal tail