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随着飞行器结构模态频率与刚性模态频率愈加接近,弹性效应对弹性飞行器飞行动力学特性的影响变得愈加明显,特别是操稳特性将变得更加的复杂和严峻,已经不能用“刚性飞行器”的分析方法进行研究,因此迫切需要为弹性飞行器建立能够包含多学科耦合的飞行动力学模型。本文对弹性飞行器飞行动力学建模的相关研究进行了总结与发展:首先简要阐述了建立多学科耦合弹性飞行器飞行动力学模型的必要性;然后对传统的弹性飞行器飞行动力学模型进行了研究,分析总结了这些方法的优缺点;最后在此基础上提出了一种新的体轴系(瞬态坐标系),并利用拉格朗日方程和有限元思想推导了该坐标系下的动力学模型,该模型克服了传统模型的缺点,并准确自然地耦合了结构动力学、飞行动力学、空气动力学与控制等学科,较现有的模型而言,该模型能更充分更全面的描述弹性飞行器飞行过程中流场、结构、控制和飞行力学之间的交叉耦合特性。本文的研究成果可为弹性飞行器的动态特性分析提供必要的理论基础。
As the modal frequencies and the modal frequencies of the aircraft structures become closer together, the effect of the elastic effect on the flight dynamics of the flexible aircraft becomes more and more obvious. In particular, the handling characteristics will become more complicated and severe, and the “ Rigid Aircraft ”research method, so there is an urgent need to establish a flexible aircraft can contain multi-disciplinary coupling dynamics model. This paper summarizes and develops the relevant research on the modeling of the flight dynamics of the flexible aircraft: Firstly, the necessity of establishing the dynamic model of the multi-disciplinary coupled elastic flying aircraft is briefly explained. Then, the traditional flight dynamics model of the flexible aircraft is studied, The advantages and disadvantages of these methods are analyzed and summarized. Finally, a new body axis system (transient coordinate system) is proposed. Based on the Lagrange equation and finite element method, the kinematics Model, which overcomes the shortcomings of the traditional model and accurately and naturally couples disciplines such as structural dynamics, flight dynamics, aerodynamics and control. Compared with the existing models, the model can be more fully and completely described Cross Coupling Characteristics of Flow Field, Structure, Control and Flight Mechanics in Elastomeric Vehicles During Flight. The research results in this paper can provide the necessary theoretical basis for the analysis of dynamic characteristics of flexible aircraft.