【作者】 王日先；

【导师】 张海波；

【作者基本信息】 南京航空航天大学 ， 航空宇航推进理论与工程， 2011， 硕士

【摘要】 飞/推综合控制技术是满足飞机先进性能要求的新一代战斗机关键技术。它把飞机和推进系统作为一个整体对象来研究,充分考虑飞机和推进系统之间的耦合作用,并通过性能优化提高推进系统潜力和协调飞行控制系统和推进控制系统等措施来改善飞机的飞行性能,从而使整个系统达到整体性能最优。本文主要围绕着飞推综合控制器设计和飞推综合优化控制两个方面进行研究的,按其内容包括以下三部分:首先建立飞推综合实时仿真模型。建立了飞机六自由度仿真模型,在原有发动机模型基础上,进行了风扇及压气机可调导叶建模工作,完善了航空发动机非线性部件级模型,然后将飞机模型和发动机模型按照飞机和发动机之间的耦合关系组合成飞/推综合模型,并对飞/推综合模型进行了稳态配平和动态仿真计算验证。其次设计飞/推综合控制规律。按照飞/推综合控制系统设计思路分别采用ADRC解耦方法和ALQR方法进行设计飞/推综合控制规律,并进行了仿真验证;其中在发动机控制系统设计时,提出了应用最小二乘方法对控制规律进行包线分区的方法解决按控制计划燃油低选问题。最后分别应用LP与SQP两种实时优化算法进行飞推综合优化控制研究。阐述了最南推力优化模式、最小油耗优化模式的优化机理及算法实现,结合飞推综合优化控制的整体设计方案,采用LP与SQP算法对以上两种优化模式进行了数字仿真,并进行了两者的性能与优化结果等方面的对比,结果表明,SQP优化方案在实时性、优化效果方面具有明显的优势。然后基于SQP实时在线优化方案,进行了飞机爬升和平飞加速任务下最南推力优化模式和飞机巡航任务下最小油耗优化模式的数学仿真验证。更多还原

【Abstract】 Integrated Flight/Propulsion control technology which used to meet the performance requirements for advanced aircraft design is one of the key technologies of a new generation fighter.It takes the aircraft and propulsion system as a whole object to study and deal with coupling effects between them. The aircraft’s closed-loop control system would turn out to be an much better integrated flight system by improving the performance of propulsion system or taking other measures to coordinate the flight control system and propulsion control system.In this paper, Integrated Flight/Propulsion System’s Controller design and optimization control are studied; According to this dissertation’s contents, three parts are as follows:First of all, the real-time model of aircraft is established for Integrated Flight/Propulsion system’s simulation. the aircraft model with six degrees of freedom is established; based on the original engine nonlinear component level model, the fan and compressor model are constructed of which the guiding vane can be adjusted, then the nonlinear component level model are better realized; according to the coupling relationship between the two models, the Plane model and the engine model are combined into the Integrated Flight/Propulsion model,and then Steady-state trimming and dynamic simulated calculation verifications are carried out for the Integrated Flight/Propulsion system’s model .Secondly,An Integrated Flight/Propulsion Controller is designed. As the design thread of Flight/Propulsion control system, ADRC decoupling method and ALQR method are respectively applied to design the Integrated Flight/Propulsion Controller, and simulation verifications are also carried out; In addition, a least square method to divide the flight envelope for some engine’s intermediate state control is proposed to solve low fuel selection principle.Finally Integrated Flight/Propulsion optimization control is studied in the use of SQP optimization algorithm and LP optimization algorithm. Mechanism and algorithm realization of maximum thrust optimization mode and minimum fuel consumption optimization mode are elaborated; simulation verifications are carried out in consideration of the design scheme of flight/propulsion optimization control of maximum thrust optimization mode in accelerating and climbing mission and minimum fuel consumption optimization mode in cruise mission.更多还原