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现代高性能战斗机均采用放宽静稳定性的布局构型,需通过先进飞行控制的设计来保证其闭环飞机在全飞行包线内均具有优良的动态特性。受到舵面操纵特性的限制,飞行控制系统的能力是有限的,即飞机本体的气动参数需满足一定的要求才能保证闭环系统的飞行品质。本文建立了研究本体气动参数对闭环飞机短周期模态特性影响规律的方法,采用等效参数准则,以基于模型参考动态逆控制律的某放宽静稳定飞机为算例,计算分析了不同本体气动参数取值大小对闭环飞机短周期模态特性的影响规律。结果表明,升降舵操纵效能是影响闭环飞机短周期模态特性的主要因素,本体气动参数需满足一定的适配关系才能保证闭环飞机具有优良的短周期飞行品质。研究方法和结果对于放宽静稳定性飞机的本体设计与飞行控制系统设计等都具有很好的参考价值。
Modern high-performance fighter planes adopt a quiet and stable layout. The advanced flight control design is required to ensure that the closed-loop aircraft has excellent dynamic characteristics in the entire flight envelope. Limited by the control surface of the control surface, the capability of flight control system is limited, that is, the aerodynamic parameters of the aircraft body must meet certain requirements to ensure the flight quality of the closed-loop system. In this paper, a method to study the effect of ontology aerodynamic parameters on the short-period modal characteristics of closed-loop aircraft is established. By using the equivalent parameter criterion, a relaxed static stabilized aircraft based on the model reference dynamic inverse control law is taken as an example, The influence of parameter value on the short-period modal characteristics of closed-loop aircraft. The results show that the control efficiency of the elevator is the main factor that affects the short-period modal characteristics of the closed-loop aircraft. The aerodynamic parameters of the body must satisfy certain adaptability to ensure the closed-loop aircraft has excellent short-period flight quality. The research methods and results have good reference value for relaxing the stability of the aircraft body design and flight control system design.