摘要
针对进近着陆过程中仪表着陆系统(ILS)受日益繁忙的空域和外界环境的干扰产生导引偏角误差,影响着陆导引精度的问题,提出一种惯性导航系统(INS)/ILS组合导航系统,以提高着陆导引性能。由ILS的调制度差(DDM)得到飞机偏离基准航道的航向偏角及下滑偏角,结合距离量测得到飞机三维位置信息,以此位置信息和:INS解算位置的差值作为量测量,运用卡尔曼滤波器对航向偏角误差和下滑偏角误差进行估计和修.1eo仿真结果表明,INS/ILS组合导航系统明显减小了ILS的偏角误差范围,航向导引偏差由0.3°减小至0.1°以内,下滑导引偏差由0.2°减小至0.1°以内;同时,组合导航系统有效抑制了ILS的位置噪声,提高了位置导引精度。
Localizer and glideslope signals in current instrument landing system （ILS） are susceptible to the environmental interference due to the increasing airspace usage during the precision approach and landing, which affects the precision of landing guidance. In order to solve this problem, we proposed an inertial navigation system （INS）/ ILS integrated navigation system in the paper, to improve the landing guidance performance. The localizer and glideslope deviations were obtained via the ILS output - difference of degree of modulation （ DDM ）, and combined DDM with distance measurement, the plane＇s three - dimensional position information was obtained. Then, measure- ments were acquired by the difference between output positions of INS and ILS. Finally, a Kalman filter was em- ployed to estimate Localizer and Glideslope deviation errors. The simulation results show that the angle error range of ILS receiver is reduced greatly through integration of INS/ILS, with the deviation range of Localizer decreased from 0. 3° to less than 0. 1° and Glideslope decreased from 0.2° to less than 0. 1~. Moreover, the integrated navigation system restraines the receiver noise in ILS effectively and the positioning accuracy is improved significantly.
出处
《计算机仿真》
CSCD
北大核心
2016年第4期95-100,共6页
Computer Simulation
基金
国家自然科学基金(L142200032)
中国工程科技长期发展战略研究(2014-zcq-01)
关键词
仪表着陆系统
惯性导航系统
组合导航
卡尔曼滤波
Instrument landing system （ ILS ）
Inertial navigation system （ INS ）
Integrated navigation
Kalman filter
