飞翼布局无人机保形非对称S弯进气道设计及优化

发布时间：2018-01-02 09:49

本文关键词：飞翼布局无人机保形非对称S弯进气道设计及优化　出处：《航空动力学报》2016年11期 　论文类型：期刊论文

【摘要】：基于国产动力约束及隐身设计要求,针对飞翼布局无人机双发动机布局进行了保形S弯进气道设计,为进一步提高进气道性能,开展了进气道优化设计研究.首先利用CFD(计算流体动力学)方法对保形进气道风洞模型进行验证,然后结合参数化建模和网格自动生成技术进行CFD数值模拟,最后利用RBF(radial basis function neural network)代理模型及多岛遗传算法开展进气道优化设计.结果表明:1优化后进气道性能有所改善,尤其表现在4°迎角之后性能明显提升,Ma=0.6下4°迎角时总压恢复系数提高了5.46%,畸变指数降低了38.7%;2优化后进气道截面积分布相比初始构型在前段更缓和而后段略微升高,中心线则在前1/3段与初始构型基本一致,之后曲率变化更加平缓;3保形进气道在出口截面具有较强的二次流,侧滑角对于此类进气道在小迎角下影响较小而大迎角时影响较大,设计时应关注大迎角时侧滑特性.
[Abstract]:Domestic power constraints and stealth design based on the requirements of the flying wing UAV twin engine layout of the conformal S shapedinlets design, in order to further improve the performance of the inlet, carried out the research on Optimization Design of the inlet. The first use of CFD (Computational Fluid Dynamics) method for verification of conformal inlet wind tunnel model, and then combined with the technology of automatic generation of parametric the CFD grid modeling and numerical simulation, finally using RBF (radial basis function neural network) inlet optimization design of agent model and multi Island genetic algorithm is carried out. The results showed that: 1 the optimization of backward airway performance improved, especially after the 4 degree angle of attack performance improved significantly, the total pressure recovery coefficient increased by 5.46% Ma=0.6 under 4 degrees when the angle of attack, the distortion index decreased by 38.7%; 2 in optimization of sectional area of distribution compared to the initial configurations in the anterior segment and then increased slightly more ease, The center line in the 1/3 section and the initial configuration is basically the same, after the curvature change more smoothly; 3 conformal inlet has two strong flow in the export section, the sideslip angle for this kind of inlet has little effect in the small angle of attack and high angle of attack is affected when the design should pay attention to sideslip characteristics at high angle of attack.

【作者单位】：中国工程物理研究院总体工程研究所;西北工业大学航空学院;
【基金】：国家自然科学基金(11302178) 航空科学基金(2013ZA53002)
【分类号】：V279;V211.48
【正文快照】： 飞翼布局无人机具有较大的升阻比和较好的隐身性能,因而越来越成为研究关注的热点,属于一种较理想的气动布局.国内外研制的无人机如X-47B、“神经元”、B2轰炸机及“暗剑”无人机等均采用翼身融合度极高的飞翼布局,具备较大装载空间,因而发动机和进气道可以深埋于机体结构内部

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