一种安装在飞行器机翼前缘的FADS系统方案研究  

Research on FADS system instrumented on wing leading edge

作　　者：方习高[1] 陆宇平[1] 鲁波[1] 

机构地区：[1]南京航空航天大学自动化学院,江苏南京210016

出　　处：《传感器与微系统》2008年第3期55-57,共3页Transducer and Microsystem Technologies

基　　金：国家高技术研究发展计划("863"计划)资助项目(2006AA705404)

摘　　要：大多数大气数据传感(FADS)系统都是采用安装在飞行器头部表面的压力传感器阵列来感受大气压力分布,为了避免FADS系统对航电系统和火控雷达系统的影响,给出了一种安装在飞行器机翼前缘的FADS系统方案,推导了其空气动力学模型,给出了上洗角的修正公式,通过风洞测试曲线和理论曲线的比较可以看出:W-FADS系统在小迎角范围内精度较好,对测量大气数据是可行的。Most FADS systems use a matrix of pressure sensors installed on the vehicle nose to measure the pressure of the vehicle surface. To avoid the FADS system＇ s effecting on the operation of the avionics or fire control radar system, a kind of FADS system which is instrumented on wing leading edge is presented, then the aerodynamic model is introduced and the upwash calibration angle is given. At last a comparison of the predicted upwash and experimentally derived upwash calibration values is presented, and it is conclude that the W-FADS system＇s performance is good during low angle of attack and it is a flexible way to measure airdata.

关 键 词：大气数据传感系统 上洗角修正 风洞测试 

分 类 号：V241[航空宇航科学与技术—飞行器设计]