Control and Stabilization Problems for Aircraft Wing Models in Subsonic Air Flow

亚音速气流中飞机机翼模型的控制与稳定问题

• 批准号: 0604842
• 负责人: Marianna Shubov
• 金额: $ 18万
• 依托单位: University of New Hampshire
• 依托单位国家: 美国
• 项目类别: Standard Grant
• 财政年份: 2006
• 资助国家: 美国
• 起止时间: 2006-06-01 至 2010-05-31
• 项目状态: 已结题
• 来源: https://www.nsf.gov/awardsearch/showAward?AWD_ID=0604842&HistoricalAwards=false
• 关键词: Control; Stabilization; Problems; Aircraft; Wing

The first main objective of this project is to carry out a detailed mathematical analysis of several control and stabilization problems for four increasingly more complete and complicated models of an aircraft wing in a surrounding air flow, and to apply the results to flutter control. The first of these models describes a long slender wing (which bends and twists) in an incompressible, subsonic, inviscid air flow. The second model is a generalization of the first one to the case of a compressible air flow. The remaining two models are the generalizations of the first two models to a wing with a movable flap (a trailing edge wing section whose angle with the main part of a wing is changing during take off and landing). The second objective of the project is to extend asymptotic and spectral analysis carried out by the investigator for the first of the above models to the other three models. The asymptotic and spectral results form the necessary basis for the solutions of all suggested control and stabilization problems. The broad goal of the entire project is to contribute to the theoretical foundations of aeroelasticity by analytical investigation of a new generation of physically realistic wing models and by analysis of the related control and stability problems.This theoretical research has practical applications to the design of mechanisms that would control and suppress flutter in aircraft wings. Flutter is the development of sudden violent vibrations of a wing, which occur in certain airspeed-altitude combinations. Flutter most commonly results in severe damage or total destruction of a wing, often leading to catastrophic failure. A significant amount of research is devoted to experimental and numerical analysis of flutter. However, theoretical analysis is essential for finding ways to design efficient methods of controlling flutter and this work develops the theoretical foundations for this problem.

本项目的第一个主要目标是对四种越来越完整和复杂的飞机机翼在周围气流中的控制和稳定问题进行详细的数学分析，并将结果应用于颤振控制。第一个模型描述了在不可压缩的、亚音速的、无粘性的气流中，一个细长的翅膀（可以弯曲和扭转）。第二个模型是第一个模型的推广，适用于可压缩气流的情况。剩下的两个模型是将前两个模型推广到带活动襟翼的机翼（在起飞和降落过程中与机翼主部分夹角发生变化的后缘机翼部分）。该项目的第二个目标是将研究者对上述第一个模型进行的渐近和谱分析扩展到其他三个模型。渐近和谱的结果构成了解决所有建议的控制和稳定问题的必要基础。整个项目的总体目标是通过对新一代物理上真实的机翼模型的分析研究以及对相关控制和稳定性问题的分析，为气动弹性的理论基础做出贡献。这一理论研究对飞机机翼颤振控制和抑制机构的设计具有实际应用价值。颤振是在一定的空速-高度组合条件下机翼突然剧烈振动的发展。颤振最常见的结果是机翼的严重损坏或完全破坏，往往导致灾难性的失败。对颤振的实验和数值分析进行了大量的研究。然而，理论分析对于设计有效的颤振控制方法至关重要，本工作为该问题奠定了理论基础。