自由飞风洞模型大迎角控制律的仿真研究

研究大迎角飞行以及大迎角控制律，是提高新一代超音速战斗机过失速超机动格斗能力的重要方面。利用自由飞风洞模型研究超音速战斗机的大迎角控制，是一种先进的仿真技术。其仿真效果和仿真水平，是一些传统的仿真方法所无法比拟的。本文介绍美国ＮＡＳＡ兰利研究中心利用直接待征结构配置法设计控制律，在３Ｏ英尺×６０英尺风洞试验室中对缩比为１４％战斗机的自由飞风洞模型人迎角控制律进行仿真研究的过程。自由飞模型试验的迎角高达８０度。驾驶员评论表明，有独创性的控制律，提供了很好的飞行品质，控制系统的鲁捧性也是令人满意的。

The Simulation of High, Angle of Attack Control law for A Free-Flight Wind Tunnel Model

It is very important to study high angle of attack flight and control laws that can enhance grapple ability of new supersonic fighter under the condition of post-stall supermaneuver. Using the freeflight wind tunnel model to study the high angle of attack control laws of supersonic flighter is an advanced simulation technique. This technique is excellent as compared with traditional simulation methods. This paper introduces a design and simulation method, which is used to develop high angle of attack flighf control laws for a 14% scale free-flight wind tunnel model of advanced fighter configuration. A Direct Eigenstructure Assignment technique is used to design control laws. The free-flight test was conducted in the NASA Langley Research Center 30-by 60-Foot Tunnel. Free-flight testing achieved up to 80 degrees angle of attack. Pilot comments indicated that the original control law design provided very good flying qualities. Control system robustness was found to be quite satisfactory.