CN-117022655-B - Power management method for aviation series hybrid electric propulsion system

Abstract

The invention discloses a power management method of an aviation series hybrid electric propulsion system. The aviation series hybrid electric propulsion system comprises an aero-engine, a generator, a battery, a motor, a transmission and a propeller, and the method introduces Yong efficiency into the aviation series hybrid electric propulsion system for the first time as an evaluation index, and optimizes a system power management scheme by combining a variable power turbine speed. Compared with the prior art, the invention can improve Yong efficiency of the aero-engine, reduce Yong loss, obtain an optimal scheme for determining expected power distribution of the aero-engine and the battery under the voyage, and improve performance of the hybrid electric propulsion aircraft.

Inventors

• GU JIANGWEI
• XI JUNJIE
• WANG YONG
• ZHANG HAIBO

Assignees

• 南京航空航天大学

Dates

Publication Date

20260508

Application Date

20230921

Claims (2)

1. 1. A power management method of an aviation series hybrid electric propulsion system comprises an aero-engine, a generator, a battery, a motor, a transmission and a propeller, and is characterized in that the maximum power is achieved by The efficiency is an optimization target, and the battery expected power of each flight task section of the aviation series hybrid electric propulsion system in the course and the power turbine rotating speed n p,i of the aviation engine are obtained by solving the following optimization model: P bat,need,min ≤P bat,need,i ≤P bat,need,max n p,min ≤n p,i ≤n p,max SOC min ≤SOC i ≤SOC max n h,i ≤n h,max T 6,i ≤T 6,max Wherein P bat,need is the expected power of the battery, n p is the power turbine speed of the aero-engine, and ψ is the aero-engine Efficiency, T f is flight time, SOC is battery charge state, n h is high-voltage shaft rotating speed of the aero-engine, T 6 is temperature before the turbine of the aero-engine, M is total number of flight task segments in the course, subscript i is flight task segment serial number, and subscripts max and min respectively represent maximum value and minimum value.
2. 2. The method of power management of an aviation series hybrid electric propulsion system of claim 1, wherein the optimization model is solved using a dynamic programming-sequence quadratic programming method.

Description

Power management method for aviation series hybrid electric propulsion system Technical Field The invention relates to a power management method, in particular to a power management method for an aviation series hybrid electric propulsion system. Background In order to promote the electrification of the aircraft propulsion system, reduce the aircraft fuel consumption and pollutant and noise emission, improve the energy conversion efficiency between each component of the aircraft propulsion system, accelerate the development of the electric propulsion aircraft technology. The technology development level of the current high-capacity energy storage system and the high-power motor is that the full-electric propulsion system facing the large-scale aircraft in the future is still in a preliminary exploration stage. Before the related technology is mature, the hybrid electric propulsion system combines the advantages of high energy density, low motor pollution and the like of the gas turbine engine, and has wide development prospect. In the tandem architecture of the hybrid electric propulsion system, the engine does not directly provide power, but drives the generator to generate electric energy to power the motor, the motor provides all the driving force of the aircraft, and the battery can be charged and discharged to provide auxiliary power. The engine can always stably operate near the optimal working point, has high efficiency and good emission performance, and is researched in various aspects and achieves staged results in view of the advantages of the series-type hybrid electric propulsion system, such as Siemens, diamond, european aviation defense and spaceflight, aeronautics and Hunan power machinery research institute. The power management serves as the core of the hybrid electric propulsion system, and the energy output of the engine and the energy storage system is distributed, so that the engine always works near a low-oil consumption area, and the purpose of improving the endurance mileage is achieved. A high quality management strategy can significantly improve the fuel economy, endurance level, and reduce pollutant emissions of an aircraft, and there is a need for power management of energy storage systems and engines based on the power requirements of the aircraft in combination with variable power turbine speeds. In the prior art, the minimum oil consumption is mostly used as an optimization target, and the conventional power management method is not combined with the variable power turbine rotating speed for optimization. Disclosure of Invention The invention aims to solve the technical problems of overcoming the defects of the prior art and providing a power management method of an aviation series hybrid electric propulsion system, which takes the maximum Yong efficiency as an optimization target and takes the expected power of a battery and the rotating speed of a power turbine of an aero engine as optimization quantities, so that the performance of the aviation series hybrid electric propulsion system can be obviously improved. The technical scheme adopted by the invention specifically solves the technical problems as follows: A power management method of an aviation serial hybrid electric propulsion system comprises an aero-engine, a generator, a battery, a motor, a transmission and a propeller, wherein the maximum Yong efficiency is used as an optimization target, and the battery expected power and the aero-engine power turbine rotating speed of each flight mission section of the aviation serial hybrid electric propulsion system in the voyage are obtained by solving the following optimization model : Wherein, the For the desired power of the battery,For the speed of the power turbine of an aero-engine,For aero-engine Yong efficiency, t f is time of flight, SOC is battery state of charge,For the high-pressure shaft rotational speed of the aero-engine,For the front temperature of the turbine of the aero-engine, M is the total number of flight mission sections in the course, the subscript i is the number of the flight mission sections, and the subscripts max and min respectively represent the maximum value and the minimum value. Preferably, the optimization model is solved using a dynamic programming-sequence quadratic programming (DP-SQP) method. Compared with the prior art, the technical scheme of the invention has the following beneficial effects: According to the invention, Yong efficiency is introduced into the aviation series hybrid electric propulsion system for the first time as an evaluation index, and the system power management scheme is optimized by combining the variable power turbine speed, so that the Yong efficiency of the aero-engine can be improved, the Yong loss is reduced, an optimal scheme for determining the expected power distribution of the aero-engine and the battery under the voyage is obtained, and the performance of the hybrid electric propulsion aircraft is impro