航空科学技术
航空科學技術
항공과학기술
AERONAUTICAL SCIENCE AND TECHNOLOGY
2015年
8期
67-72
,共6页
S弯进气道%微质量射流%总压恢复%畸变%隐身无人机%飞翼%多目标优化
S彎進氣道%微質量射流%總壓恢複%畸變%隱身無人機%飛翼%多目標優化
S만진기도%미질량사류%총압회복%기변%은신무인궤%비익%다목표우화
S-shape inlet%micro-mass jets%total pressure recovery%distortion%stealth UAV%all-wing aircraft%multi-objectives%optimization
在S弯进气道设计点，针对前机身/进气道一体化模型，采用CFD数值模拟技术开展内外流计算，分析管道内流场特性从而为流动控制装置设计提供参考依据。采用微质量射流流动控制装置对进气道内流进行流动控制，射流装置可变参数包括射流装置安装站位、入射流向角度、侧向角度及射流孔间距。基于DOE方法设计控制效能计算样本，开展流动控制效能计算分析，得到总压恢复系数σ及流场畸变指标DC60的响应面函数，采用多目标优化技术，得到使得总压恢复比较高、流场畸变比较小的控制装置参数Pareto最优解。
在S彎進氣道設計點，針對前機身/進氣道一體化模型，採用CFD數值模擬技術開展內外流計算，分析管道內流場特性從而為流動控製裝置設計提供參攷依據。採用微質量射流流動控製裝置對進氣道內流進行流動控製，射流裝置可變參數包括射流裝置安裝站位、入射流嚮角度、側嚮角度及射流孔間距。基于DOE方法設計控製效能計算樣本，開展流動控製效能計算分析，得到總壓恢複繫數σ及流場畸變指標DC60的響應麵函數，採用多目標優化技術，得到使得總壓恢複比較高、流場畸變比較小的控製裝置參數Pareto最優解。
재S만진기도설계점，침대전궤신/진기도일체화모형，채용CFD수치모의기술개전내외류계산，분석관도내류장특성종이위류동공제장치설계제공삼고의거。채용미질량사류류동공제장치대진기도내류진행류동공제，사류장치가변삼수포괄사류장치안장참위、입사류향각도、측향각도급사류공간거。기우DOE방법설계공제효능계산양본，개전류동공제효능계산분석，득도총압회복계수σ급류장기변지표DC60적향응면함수，채용다목표우화기술，득도사득총압회복비교고、류장기변비교소적공제장치삼수Pareto최우해。
CFD simulation was conducted to simulate inner and outer lfow ifelds of S-shape inlet on design points for fore-fuselage and inlet integration model, and inner flow field performance was analyzed to provide referent basis to lfow control device design. Micro-mass jet control device was adopted to control inlet inner lfow ifeld, with changeable parameters: device installation location, inlfow stream-wise angles, lateral angles and the spaces between jet oriifces. Flow control efifciency computation samples were designed based on DOE method, and control efifciency computation analysis was conducted to get the response surface function of total pressure recovery coefficientσ and flow field distortion index DC60. Multi-objectives technology is used to obtain the Pateto optimum solution of control device parameter with higherσand DC60 lower .
