无尾布局嵌入式舵面的大迎角纵向操纵能力研究

 针对某前掠翼翼身融合无尾布局由鸭面与尾舵组成的纵向基本控制舵面在大迎角状态操纵效率降低的问题,采用数值模拟方法研究一种机身下表面嵌入式新概念纵向操纵舵面实施大迎角纵向操纵补充的可行性。提出了嵌入式舵面的设计思想,研究了嵌入式舵面高度、偏度及其与尾舵组合时的相对位置等参数影响,提出了嵌入式舵面的设计原则、流动机理以及提供低头力矩增量的作用原理。研究结果表明:嵌入式舵面是无尾布局飞机大迎角纵向操纵的高效补充措施,单独使用,最大可提供约平衡10°迎角的低头操纵力矩,并对升阻特性影响很小;与尾舵组合使用,在研究迎角范围内(迎角α≤32°),可提供约6°迎角的低头平衡力矩增量,且对升阻性能产生有利影响。本文工作可为其他翼身融合无尾布局的气动舵面设计提供借鉴。

Longitudinal Control Ability Investigation of Lower Surface Spoiler for Blended Wing Body Tailless Configuration at High Angles of Attack

Based on the platform of blended wing body tailless configuration,to solve the problem of decreasing pitching control efficiency at high angles of attack for basic longitudinal control surfaces including canard elevator and tail elevator,the new concept of lower surface spoiler is put forward and the effectiveness and auxiliary function for pitching control at high angles of attack is analyzed with numerical simulation method.The influences of the parameters such as lower surface spoiler’s height,deflection angle,and relative position when combined with tail elevator are studied.The design law,flow mechanism and action principle to afford nose-down pitching moment increment are put forward.The results show that lower surface spoiler can support tailless configuration as a high-efficiency longitudinal control effecter.With the single use of lower surface spoiler,the maximal nose down pitching moment can be obtained to balance 10° angle of attack with little effect on lift and drag characteristics.When combined with the tail elevator,nose down moment increment of 6° angle of attack can be obtained with the angles of attack smaller than 32° and favorable effect on lift-drag performance is produced.The longitudinal control ability at high angles of attack is improved.The design developed in this paper can provide a reference for control surface design for blended wing body tailless configuration.