The invention discloses an electric-thermal energy management optimization method for an electric propulsion system of a hybrid aircraft, and belongs to the field of energy management. The method comprises the following steps: optimizing the electric propulsion system of the hybrid aircraft by adopting a multidisciplinary optimization design method; based on the hybrid aircraft electric propulsion system, an electric-thermal management system of the hybrid aircraft electric propulsion system is constructed; the hybrid aircraft electric propulsion system electric-thermal management system comprises a lithium ion battery electric-thermal coupling model and a motor thermal model, and thermal management of the hybrid aircraft electric propulsion system is achieved through a thermal management assembly. An electric-thermal energy comprehensive management and optimization strategy of the electric propulsion system of the hybrid aircraft is constructed based on the MPC, fuel economy and temperature are taken as optimization targets, the minimum value of a target function is solved by utilizing MPC rolling optimization control under each flight profile, and accurate distribution of power and control of temperature are realized. According to the invention, accurate distribution of power and effective control of key component temperature can be realized.
本发明一种混合动力飞机电推进系统电‑热能量管理优化方法,属于能量管理领域;方法步骤为:采用多学科优化设计方法对混合动力飞机电推进系统进行优化;基于混合动力飞机电推进系统,构建混合动力飞机电推进系统电‑热管理系统;所述混合动力飞机电推进系统电‑热管理系统包括锂离子电池电‑热耦合模型与电机热模型,通过热管理组件实现对混合动力飞机电推进系统的热管理;基于MPC构建混合动力飞机电推进系统电‑热能量综合管理与优化策略,以燃油经济性和温度为优化目标,在每个飞行剖面下利用MPC滚动优化控制求解目标函数的最小值,实现功率的精确分配和温度的控制。本发明能够实现功率的精确分配和关键组件温度的有效控制。
Electric-thermal energy management optimization method for electric propulsion system of hybrid aircraft
一种混合动力飞机电推进系统电-热能量管理优化方法
2025-04-25
Patent
Electronic Resource
Chinese