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首页> 外文期刊>Journal of Aeronautics & Aerospace Engineering >Flight Dynamics and Control of a Vertical Tailless Aircraft
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Flight Dynamics and Control of a Vertical Tailless Aircraft

机译：垂直无尾飞机的飞行动力学和控制

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The present work aims at studying a new concept of a vertical tailless aircraft provided with a morphing tail solution with the purpose of eliminating the drag and weight created by the vertical tail structure. The solution consists on a rotary horizontal tail with independent left and right halves to serve as control surfaces. Different static scenarios are studied for different tail configurations. The proposed morphing configurations are analyzed in terms of static and dynamic stability and compared with a conventional configuration. The stability derivatives defining the limits of static stability are calculated for the whole range of tail rotation angles. The aircraft's dynamic model is developed and feedback control systems are implemented. A sideslip suppression system, a heading control system and a speed and altitude hold system are studied for three different configurations, MC1, MC2 and MC3 configurations. Static results show that the aircraft is longitudinally stable for a wide range of tail rotation angles. Variation of tail dihedral and rotation angles are two mechanisms able to maintain directional and lateral stability but only the last is able to produce lateral force and yawing moment. Dynamic stability results demonstrate no spiral nor Dutch-roll modes due to the absence of the vertical stabilizer. The increase in tail rotation produces an appearance of the spiral mode and an unstable Dutch-roll mode that quickly degenerates into two unstable real roots with the increase in tail rotation. The addition of dihedral to the tail increases the stability of the overall modes while decreasing their variation amplitude with the tail rotation. The morphing tail configuration proved to be a feasible control solution to implement in an aircraft such as a small UAV, with the MC1 configuration being the most simple of the three morphing configurations and also the most reliable one.
机译：本工作旨在研究一种具有变型尾翼解决方案的垂直无尾飞机的新概念，以消除垂直尾翼结构产生的阻力和重量。该解决方案包括一个旋转的水平尾巴，该尾巴具有独立的左右两半，以用作控制表面。针对不同的尾部配置研究了不同的静态方案。根据静态和动态稳定性分析了建议的变形配置，并与常规配置进行了比较。为整个尾部旋转角度范围计算定义静态稳定性极限的稳定性导数。开发飞机的动态模型并实施反馈控制系统。针对三种不同的配置（MC1，MC2和MC3配置），研究了侧滑抑制系统，航向控制系统以及速度和高度保持系统。静态结果表明，该飞机在很宽的尾旋角范围内都能保持纵向稳定性。尾部二面角和旋转角度的变化是两种能够保持方向和横向稳定性的机制，但只有最后一种能够产生横向力和偏航力矩。动态稳定性的结果表明，由于没有垂直稳定器，因此没有螺旋和荷兰语模式。尾巴旋转的增加会产生螺旋模式和不稳定的荷兰卷模式，随着尾巴旋转的增加，该模式迅速退化为两个不稳定的实根。向尾部添加二面角可提高总体模式的稳定性，同时减小其随着尾部旋转的变化幅度。变形尾翼配置被证明是在诸如小型无人机等飞机上实施的可行控制解决方案，其中MC1配置是三种变形配置中最简单的配置，也是最可靠的一种。

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