导弹与航天运载技术
導彈與航天運載技術
도탄여항천운재기술
MISSILES AND SPACE VEHICLES
2013年
2期
1-7
,共7页
高超声速%临近空间%气动热力学%数值仿真计算%轨迹优化与总体飞行仿真
高超聲速%臨近空間%氣動熱力學%數值倣真計算%軌跡優化與總體飛行倣真
고초성속%림근공간%기동열역학%수치방진계산%궤적우화여총체비행방진
Hypersonic%Near space%Aerothermodynamics%Numerical simulation and calculation%Trajectory optimization and overall flight simulation
采用计算流体力学(CFD)方法获得不同工况下飞行器流场的气动特性.通过对多个工况点下流场热力学状态的分析与对比,给出高超声速飞行器飞行过程中的热流密度、温度场与气动特性的数值分布,并依据这些数据对飞行器的上升段、巡航段和俯冲段进行飞行轨迹的一体化优化设计与总体飞行仿真.
採用計算流體力學(CFD)方法穫得不同工況下飛行器流場的氣動特性.通過對多箇工況點下流場熱力學狀態的分析與對比,給齣高超聲速飛行器飛行過程中的熱流密度、溫度場與氣動特性的數值分佈,併依據這些數據對飛行器的上升段、巡航段和俯遲段進行飛行軌跡的一體化優化設計與總體飛行倣真.
채용계산류체역학(CFD)방법획득불동공황하비행기류장적기동특성.통과대다개공황점하류장열역학상태적분석여대비,급출고초성속비행기비행과정중적열류밀도、온도장여기동특성적수치분포,병의거저사수거대비행기적상승단、순항단화부충단진행비행궤적적일체화우화설계여총체비행방진.
The aerodynamic characteristics of flight vehicle flow field under different working conditions were obtained with computational fluid dynamics (CFD). Through analysis and comparison of flow field thermodynamic state under multiple operating points, the numerical distribution of the heat flux value, temperature field and aerodynamic characteristics in the course of hypersonic flight was presented. Based on these data, integrated optimization design of the trajectory and the overall flight simulation were conducted for the ascent stage, cruising stage and diving stage of the vehicle.
