期刊文献+

考虑模态转换的组合动力飞机任务性能快速评估方法

A Fast Evaluation Method for Mission Performance of Combined Cycle Engine Aircraft Considering Mode Transition
下载PDF
导出
摘要 工作在较宽飞行范围的高马赫数组合动力飞机,其动力性能受到飞行条件/飞行姿态以及模态转换的影响,并进一步影响其飞行任务性能。为尽可能真实并快速地评估组合动力飞机的飞行任务性能,提出了一种考虑模态转换的组合动力飞机任务性能快速评估方法,并量化研究了不同飞行轨迹、不同模态转换区间对飞行任务性能的影响。首先建立了高马赫数飞机的飞行动力学模型,将飞行姿态考虑进任务分析中;随后建立了组合动力的非安装及安装性能计算模型,飞行轨迹中可实时模拟动力装置的性能;最后建立了模态转换模拟模型,可分析模态转换过程对飞行任务性能的影响。结果表明:该文研究的飞行马赫数为5的组合动力飞机,巡航高度由海拔20 km升高至27 km,巡航距离增加18.3%,总航程增加21.9%;将模态转换马赫数区间由低马赫数2~2.3向高马赫数2.2~2.5范围移动,爬升加速段距离增加8.4%,爬升加速时间增加5.8%。 The propulsive performance of a high Mach-number combined cycle engine aircraft(CCEA)operating in a wide flight-range is affected by the flight conditions/attitude and mode transition,which further affects the flight mission performance.In order to evaluate the mission performance of the combined cycle engine aircraft as real and fast as possible,a fast evaluation method of the combined power aircraft mission-performance considering the mode transition was proposed,and the effects of different flight envelopes and different mode transition intervals on the flight mission performance were quantitatively studied.Firstly,the flight dynamics model of high Mach-number aircraft was established,and the flight attitude was taken into account in the mission analysis.Then the calculation model of non-installed and installed performance of the combined cycle engine was established,which can simulate the performance of the engine in real time in the flight envelop.Finally,a modal transition simulation model was established to analyze the effect of modal transition process on flight performance.The results indicate that the cruising altitude of the studied CCEA with Mach number of 5 increases from 20 km to 27 km,and increases by 18.3%.The total range increases by 21.9%.Furthermore,the modal transition interval shifts from low Mach numbers(Ma=2-2.3)to high Mach numbers(Ma=2.2-2.5).The climbing acceleration distance increases by 8.4%;the climbing acceleration time increases by 5.8%.
作者 付昱 宋文艳 汪秋吟 FU Yu;SONG Wenyan;WANG Qiuyin(School of Power and Energy,Northwestern Polytechnic University,Xi’an 710072,China)
出处 《弹道学报》 CSCD 北大核心 2024年第1期1-9,共9页 Journal of Ballistics
基金 四川燃气涡轮研究院项目 高超声速冲压发动机重点实验室项目(STS/MY-ZY-2018-009)。
关键词 高马赫数飞机 组合动力 模态转换 飞行轨迹 飞行任务性能 high Mach-number aircraft combined cycle engine mode transition flight trajectory flight mission performance
  • 引文网络
  • 相关文献

参考文献7

二级参考文献30

共引文献32

;
使用帮助 返回顶部