民机飞行特情状态预测及改出控制研究

发布时间：2018-10-20 12:37

【摘要】：民机飞行特情对飞行安全构成严重威胁。随着飞机本体安全性的提高,由大气扰动诱发的飞行特情的比例不断上升。飞机在大气扰动下执行预定飞行任务时,如何保持飞行状态参数在安全飞行包线内,是保证飞行安全的关键。论文基于某民机建模数据,建立完整的飞行动力学模型和线性变参数模型。并以安全改出飞行特情为目标,研究基于滚动优化的控制律算法,并专门针对飞机处于外部干扰情况下的下滑道捕获与跟踪的控制策略进行探讨。论文的主要研究内容有:(1)建立了全量非线性飞机动力学模型。基于民机建模数据,系统分析并建立了气动力和力矩模型,以及自动飞行控制系统模型,并结合验模数据进行了模型验证。全量模型已获得工程应用。(2)建立了用于民机起降阶段飞行特情分析的动力学模型。系统推导了含扰动风的近地面飞行动力学方程,建立起落架模型以用于飞机异常接地过程模拟。结合某民机建模数据和飞行记录数据,实现了该机重着陆和扰动风下擦地复飞的事故过程再现。(3)建立了用于下滑道捕捉与跟踪的纵向线性变参数LPV模型。系统分析了典型飞行状态下各项气动导数对空气动力和力矩的影响,获得简化三自由度模型。采用函数替代方法,建立了飞机纵向三自由度的LPV模型,并完成了模型验证仿真。(4)针对飞机进场着陆过程,采用模型预测控制方法完成控制器设计。在LPV模型的基础上,从飞行包线保护的角度,研究了飞机在扰动风影响下进场着陆的预测控制方法。并通过飞机下滑道跟踪仿真,验证了控制器的有效性。
[Abstract]:The special situation of civil aircraft flight poses a serious threat to flight safety. With the improvement of aircraft body safety, the proportion of special flight conditions induced by atmospheric disturbance is increasing. How to keep the flight state parameters in the safe flight envelope is the key to ensure the flight safety when the aircraft performs a scheduled flight mission under the atmospheric disturbance. Based on the modeling data of a civil aircraft, a complete flight dynamics model and a linear variable parameter model are established in this paper. The control law algorithm based on rolling optimization is studied, and the control strategy of glide track acquisition and tracking in the case of external interference is discussed. The main contents of this paper are as follows: (1) A total nonlinear aircraft dynamics model is established. Based on the modeling data of civil aircraft, the aerodynamic force and torque model and the model of automatic flight control system are analyzed and established. The total model has been applied in engineering. (2) A dynamic model is established for the analysis of flight characteristics in the take-off and landing stages of civil aircraft. The dynamic equations of near-ground flight with disturbance wind are derived systematically, and the landing gear model is established to simulate the abnormal grounding process of aircraft. Combined with the modeling data and flight record data of a civil aircraft, the accident process of aircraft landing and earth-scraping under disturbed wind is reappeared. (3) the longitudinal linear variable parameter LPV model for glide track capture and tracking is established. The effects of aerodynamic derivatives on aerodynamic force and torque in typical flight state are systematically analyzed, and a simplified three-degree-of-freedom model is obtained. The LPV model of aircraft longitudinal three degrees of freedom is established by using function substitution method, and the model verification simulation is completed. (4) Model predictive control method is used to complete the controller design for the approach and landing process of aircraft. Based on the LPV model, the predictive control method for the approach landing of aircraft under the influence of disturbance wind is studied from the angle of flight envelope protection. The effectiveness of the controller is verified by the aircraft glide track simulation.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V249;V212.1

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