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首页> 外文期刊>International journal of aerospace engineering >Adaptive Differential Thrust Methodology for Lateral/Directional Stability of an Aircraft with a Completely Damaged Vertical Stabilizer
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Adaptive Differential Thrust Methodology for Lateral/Directional Stability of an Aircraft with a Completely Damaged Vertical Stabilizer

机译：具有完全损坏的垂直稳定器的飞机横向/方向稳定性的自适应微分推力方法

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This paper investigates the utilization of differential thrust to help a commercial aircraft with a damaged vertical stabilizer in order to regain its lateral/directional stability. In the event of an aircraft losing its vertical stabilizer, the consequential loss of the lateral/directional stability and control is likely to cause a fatal crash. In this paper, an aircraft with a completely damaged vertical stabilizer is investigated, and a unique differential thrust-based adaptive control approach is proposed to achieve a stable flight envelope. The propulsion dynamics of the aircraft is modeled as a system of differential equations with engine time constant and time delay terms to study the engine response time with respect to a differential thrust input. The proposed differential thrust control module is then presented to map the rudder input to differential thrust input. Model reference adaptive control based on the Lyapunov stability approach is implemented to test the ability of the damaged aircraft to track the model aircraft's (reference) response in an extreme scenario. Investigation results demonstrate successful application of such differential thrust approach to regain lateral/directional stability of a damaged aircraft with no vertical stabilizer. Finally, the conducted robustness and uncertainty analysis results conclude that the stability and performance of the damaged aircraft remain within desirable limits and demonstrate a safe flight mission through the proposed adaptive control methodology.
机译：本文研究了利用不同推力来帮助垂直稳定器受损的商用飞机，以恢复其横向/方向稳定性。在飞机失去垂直稳定器的情况下，横向/方向稳定性和控制性的相应损失很可能导致致命的坠毁。在本文中，研究了具有完全损坏的垂直稳定器的飞机，并提出了一种独特的基于差推力的自适应控制方法来实现稳定的飞行包线。飞机的推进动力学建模为具有发动机时间常数和时间延迟项的微分方程系统，以研究相对于差分推力输入的发动机响应时间。然后提出建议的差动推力控制模块，以将舵输入映射到差动推力输入。实施了基于Lyapunov稳定性方法的模型参考自适应控制，以测试受损飞机在极端情况下跟踪模型飞机（参考）响应的能力。研究结果表明，这种差动推力方法成功地用于恢复没有垂直稳定器的受损飞机的横向/方向稳定性。最后，进行的鲁棒性和不确定性分析结果表明，受损飞机的稳定性和性能保持在理想的范围内，并通过提出的自适应控制方法论证了飞行任务的安全性。

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