宋寒冰,夏明.一种利用尾舵偏转实现BWB飞机减速的方法[J].民用飞机设计与研究,2019,(4):36-40
一种利用尾舵偏转实现BWB飞机减速的方法
  
DOI:10.19416/j.cnki.1674-9804.2019.04.006
中文关键词:翼身融合飞机  尾舵偏转  减速
英文关键词:BWB airplane  tail deflection  deceleration
基金项目:
作者单位
宋寒冰,夏明 中国商飞北京民用飞机技术研究中心北京 102211 
中文摘要:结合国内外的相关研究工作,提出了一种利用尾舵偏转实现BWB飞机发动机喷气气流方向的改变,进而达到减速目的的方法。基于求解三维欧拉法方程,数值模拟了不同尾舵偏转角度下BWB飞机发动机喷口附近的流场分布特性和反推力大小,并评估了着陆场长收益。气动与性能计算结果表明,在计算滑跑速度范围内,发动机喷气气流会冲击到偏转的尾舵上,进而产生反向喷气气流,并产生较大的反推力,有效降低着陆场长,且随着尾舵偏转角度的增加,反推和减速效果逐渐增大。
英文摘要:Combined with the related research work both domestic and overseas, this paper proposes a method to realize the direction change of the airflow from the BWB(Blended Wing Body)) aircraft engine by deflecting the horizontal tail, as consequence to achieve the deceleration purpose. Based on solving the three-dimensional Euler’s equation, the flow field distribution characteristics and reverse thrust near the nozzle of BWB aircraft under different tail deflection angles are numerically simulated, and the gain in landing field length is evaluated. Aerodynamic and performance calculations show that, within the speed limit, the engine jet airflow will impact the deflected tail, which will generate a reverse jet flow and generate a large reverse thrust, effectively reducing the landing field length. And as the deflection angle of the tail increases, the reverse thrust and deceleration effects gradually increase.
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