摘要
运载火箭上升段存在强脉动压力载荷引起的跨声速抖振问题。抖振载荷预示主要基于风洞试验,然而风洞试验与飞行遥测数据存在差异,这将极大影响对运载火箭总体性能的预判。从脉动压力物理机理出发,对飞行遥测数据进行了修正,并从雷诺数、声环境、数据样本等方面进行了天地数据差异性分析和研究。研究结果表明:1)运载火箭飞行动力学符合准稳态过程;2)飞行和风洞脉动压力载荷遵循气动相似定律;3)声环境差异影响载荷谱的高频范围。因此,风洞试验仍然是预示火箭抖振载荷的有效手段。
Launch vehicles experience transonic buffet induced by intense fluctuating pressure loads during atmospheric ascent.Buffet load prediction is predominantly based on fluctuating pressure wind tunnel testing.However,the unclear correlation between flight and wind-tunnel test fluctuation pressure data significantly impacts overall performance estimation for launch vehicles.Based on the physical mechanisms of fluctuating pressure,this study calibrates flight fluctuating pressure data,followed by comprehensive flight-wind tunnel discrepancy analysis encompassing Reynolds number effects,acoustic environments,and data sampling accuracy.Key findings indicate:1)Launch vehicle flight dynamics conform to quasi-steady processes.2)Flight and wind-tunnel fluctuating pressure loads follow aerodynamic similarity laws.3)Acoustic environment discrepancies affect the high-frequency range of load spectra.Thus,wind tunnel testing remains a validated methodology for predicting launch vehicle buffet loads.
作者
赵磊
张耘隆
季辰
刘畅
闫指江
ZHAO Lei;ZHANG Yunlong;JI Chen;LIU Chang;YAN Zhijiang(China Academy of Aerospace Aerodynamics,Beijing 100074,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)
出处
《宇航总体技术》
2025年第6期22-30,共9页
Astronautical Systems Engineering Technology
基金
国家自然科学基金(U23B6009)。
关键词
脉动压力
跨声速
抖振
飞行试验
风洞试验
Fluctuating pressure
Transonic
Buffeting
Flight test
Wind tunnel test
