联接翼布局直接升力控制特性的初步研究  

An Approach to the Direct Lift Control Characteristics on the Joined Wing Configuration

作　　者：潘家正[1] 吕庆风[1] 周欲晓[1] 

机构地区：[1]南京航空航天大学

出　　处：《空气动力学学报》1996年第4期441-447,共7页Acta Aerodynamica Sinica

基　　金：航空科学基金

摘　　要：本文对联接翼气动布局的直接升力控制特性进行了初步的探索。通过前、后机翼上升降舵面的同向偏转组合所产生的直接升力，与相应的正常布局相比较，不仅显示了飞机优异的气动性能：增加了最大升力系数和升力线斜率，改善了失速特性，提高了纵向静稳定性，而且明显改善了ΔＣｙ、Δｎｙ、ΔＨ、ωｚ等参数对操纵输入的瞬态响应品质，给飞机提供独立的姿态或轨迹控制的非同寻常的运动模态。头部鸭翼的增加进一步提高和改善了联接翼布局的直接升力特性。This paper presents an approach to the direct lift control characteristics on the joined wing configuration. The direct lift produced by the same direction deflection combination of control faces on front and rear wings, comparing with the relevant normal configuration, not only shows the outstanding longitudinal aerodynamical performance of aircraft:enhance of the maximum lift coefficient and lift slope,improvement of the stall characteristics, increase of the longitudinal static stability, but also evidently improves the instantaneous response quality to the control input of the such parameters as ΔC_y, Δn_y, ΔH, ω_z,etc.,and can provide unique modes about independent attitude or path control to aircraft motion. The added front canard increases the direct lift characteristics of the joined wing configuration.

关 键 词：联接翼 布局 直接升力控制 飞机空气动力学 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计] V211.4