低RCS飞行器外形设计实践  

CONTOUR DESIGN AND PRACTICE FOR A LOW RCS 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,南京210016

出　　处：《航空学报》1995年第6期692-701,共10页Acta Aeronautica et Astronautica Sinica

摘　　要：在鸭式布局的基础上 ,对飞行器各部件及部件间的连接方式进行了外形隐身设计。对初步形成的鸭翼 -翼身融合体改变机身头部形状和立尾配置等进行 RCS优化。给出了飞行器各种状态下的 RCS平均值和迎头± 45°区内的 RCS值。测试结果表明 ,尖头机身、 30°双立尾 (立尾与垂直平面成± 30°角 )的鸭翼 -翼身融合体的 RCS值最小。对 RCS优化后的外形 ,风洞测力试验表明其气动性能也较好 (最大升阻比达到 8,失速迎角超过 2 6°)On the basis of the canard configuration a contour stealthy design including chiefly the wing, the fuselage and their connection type is projected. A prime project of a blended wing body vehicle with canard is provided, and through the change of the fuselage head form and the different fin disposals, the RCS are optimized. The average value of RCS and the value of RCS in the ±45°front sector for different designs are illustrated. The model measurement proved that the project having a sharp head fuselage and 30°double fin has the minimum value of RCS. The wind tunnel test to the model with RCS optimized proved that the vehicle project has excellent aerodynamic characteristics such as high lift curve slope, up to 26° stalling angle, high lift/drag ratio equal to 8, etc.

关 键 词：飞机设计 雷达载面 风洞试验 隐身技术 鸭式 

分 类 号：V218[航空宇航科学与技术—航空宇航推进理论与工程] V221.3