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首页> 外文期刊>CEAS Aeronautical Journal >Controllability of an aircraft with active high-lift system using a segmentwise controllable flap system
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Controllability of an aircraft with active high-lift system using a segmentwise controllable flap system

机译：使用分段可控襟翼系统的主动高升力系统飞机的可控性

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摘要

Active high-lift aircraft needs exceptional aerodynamic control performance to operate at low airspeed. In this study, a new concept for the improvement of controllability is investigated, incorporating the special capabilities of a blown Coanda flap system. The blowing system along the flaps is divided into 12 independently controllable segments. This provides the opportunity to influence the lift distribution along the wingspan by individual blowing performance settings for each segment without changing the flap deflection. This offers the chance to control the airplane in the final approach phase with fully deflected flaps using only the blowing system and to dedicate specific control tasks to particular segments. A model for the blowing system influence on the local wing aerodynamics is implemented in an existing nonlinear full aircraft flight mechanics model. The system capabilities in terms of roll control and the climb performance are investigated by criteria' evaluation and dynamic simulation assessment. The ability to fly turn/altitude change maneuvers by utilizing the active high-lift system is proven and a corresponding control concept is presented. It also includes the compensation of different blowing failure cases, which leads to acceptable but still improvable aircraft reactions.
机译：主动式高升力飞机需要出色的空气动力学控制性能才能在低空速下运行。在这项研究中，结合吹制的柯恩达襟翼系统的特殊功能，研究了一种提高可控性的新概念。沿风门的吹气系统分为12个独立可控的部分。这提供了机会，通过改变每个扇形段的单独吹气性能设置来影响沿翼展的升力分布，而无需改变襟翼的偏转。这提供了在最后进场阶段使用仅偏转的襟翼完全偏转的襟翼来控制飞机的机会，并将特定的控制任务专用于特定的部分。在现有的非线性全飞机飞行力学模型中，实现了吹塑系统对局部机翼空气动力学影响的模型。通过标准评估和动态仿真评估研究了侧倾控制和爬升性能方面的系统功能。通过使用主动式高升力系统，可以实现转弯/高度变更操纵的能力，并提出了相应的控制概念。它还包括对不同的吹气失败情况的补偿，这会导致可接受但仍可改善的飞机反应。

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