低RCS无人驾驶飞行器的外形设计与实验研究  

The Contour Design and Test Studyfor a Low RCS Remotely Piloted Vehicle

作　　者：王略[1] 章仲安[1] 

机构地区：[1]南京航空航天大学无人机研究所

出　　处：《南京航空航天大学学报》1994年第1期17-26,共10页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：本文基于缩比模型在低速风洞中作纵、横向测力试验及微波暗室中ＲＣＳ的测试数据分析，论述了一种供选型用鸭式布局翼身融合体飞行器外形初步设计方案的可行性。测试结果表明，小展弦比大后掠角带边条的翼身融合体在配置与不配置鸭翼情况下，均具有良好的气动特性，如较大的升力线斜率，高达２６°的失速迎角、较大的纵向和横侧向静稳定度及较高的升阻比等。同时也具有良好的雷达隐身性能，如在迎头土４５°扇区内ＲＣＳ的平均值约为─１４ｄＢ左右，采用外倾式双垂尾使侧向ＲＣＳ峰值急剧降低等。本文所提供的飞行器设计图及测试结果分析均具有工程参考价值。This paper discusses the feasibility for a prime project of blended wing body vehicle of canard configuration as a selected type tested in the model wind tunnel for the longitudinal and lateral aerodynamic characteristics; and the measurement data of radar cross section (RCS) are analyzed in an anechoic chamber.The test results prove that, a small aspect ratio and high sweep-back blended windbody configuration with streak placed around canard wing has both excellent aerodynamic characteristics, such as high lift curve slope q up to 26° stalling angle, high longitudinal and lateral stability, and it also has excellent stealthy performance, such as the average value of RCS in the t45' front sector is about 14 dBsm, and the rapid decrement of the lateral RCS value by use of double fin with the dip angle out of the perpendicular, etc.The vehicle project and its test measurement data given by this paper are valuable for reference.

关 键 词：无人驾驶飞机 气动特性 风洞试验 

分 类 号：V279[航空宇航科学与技术—飞行器设计]