基于多导航源融合的下滑道稳定性控制  

Glideslope Stability Control Based on the Fusion of Multi-Navigation Sources

作　　者：肖川[1,2] 岳晓奎[2] 王永虎[1] 

机构地区：[1]中国民航飞行学院,四川广汉618307 [2]西北工业大学,西安710072

出　　处：《计算机测量与控制》2014年第8期2459-2462,2465,共5页Computer Measurement &Control

基　　金：国家自然科学基金委-中国民航局联合资助项目(U1333133)

摘　　要：下滑道构型畸变将造成航空器进近不稳定,严重时将导致航空器俯仰姿态过大,低高度失速或下降率超限等不安全事故;针对以上问题,在传统仪表着陆系统的基础上,提出了基于惯导、气压高度表和卫星导航等多导航源融合的下滑道稳定性控制模型,采用卡尔曼滤波进行数据融合,解决了下滑道畸变情况下航空器水平位置与高度匹配性差的难点并进行了可行性分析,避免了航空器追随畸变下滑台信号而带来的进近不稳定,最后对所建模型进行了航空器下滑轨迹仿真;结果表明该模型有效地增强了下滑道的稳定性,提高了航空器进近成功率,进一步保证了飞行安全。The unstable approach caused by the distortion of glideslope endangers aircraft in the forms of over--pitching, stalling at low altitude, and exceeding the limitation of descent rate. Aiming at the issues above, in addition to the conventional instrument landing system, a glideslope stability control model based on the fusion of multi--navigation sensors, INS, Baro--altimeter and GNSS is proposed, and kalman filtering is employed for data fusion to solve the mismatch between the horizontal position and the actual vertical position which avoids the descent instability in the case of glidestope distortion. Finally, model simulations on glide path have been done to prove the effectiveness of the model, and the results show that the control model can enhance the stability of glideslope effectively, promote the success rate of approach, and ensure the flight safety.

关 键 词：多导航源融合 下滑道畸变 调制度差 惯性导航 气压高度表 卫星导航 

分 类 号：V241.62[航空宇航科学与技术—飞行器设计]