民用航空惯性基准系统重力补偿方法  

Gravity Compensation Method for Inertial Reference System of Civil Aviation

作　　者：王鑫耀 李荣冰 刘刚[2] 刘建业 WANG Xin-yao;LI Rong-bing;LIU Gang;LIU Jian-ye(Navigation Research Center,Nanjing University of Aeronautics and Astronautics,Nanjing 211106;AVIC Xi’an Flight Automatic Control Research Institute,Xi'an 710065)

机构地区：[1]南京航空航天大学导航研究中心,南京211106 [2]航空工业西安飞行自动控制研究所,西安710065

出　　处：《导航与控制》2022年第1期49-56,共8页Navigation and Control

摘　　要：惯性基准系统在民用航空中是位置、速度、姿态等信息的核心信息源,由于民用航空领域安全关键的特性,要求惯性基准系统具备在短时间内不依赖卫星辅助独立完成导航工作并保持可靠性能的能力。针对重力模型误差在高精度惯性基准系统纯惯性运行期间对定位精度影响显著的问题,研究了基于高阶重力球谐模型EGM2008的重力补偿方法,提升了定位精度和对所需导航性能(Required Navigation Performance,RNP)的支持能力。面向受约束的应用场景,进一步分析了模型阶次与性能优化的关系,为高阶球谐重力模型在工程中的应用提供了参考。仿真结果表明,重力补偿使20min纯惯性运行的水平定位精度提升了61%,裁剪模型在保证精度性能的同时可获得97%的计算效率优化,验证了其可行性和有效性。Inertial reference system is the core information source for position,velocity,attitude and other information in civil aviation.Due to the safety-critical nature of civil aviation,inertial reference system is required to have the ability to complete navigation independently and maintain reliable performance in a short period of time without r1 elying on assistance of satellite.Aiming at the problem that the gravity error has a significant impact on the accuracy during the pure inertial operation of the high-precision inertial reference system,based on the high-order spherical harmonic gravity model EGM2008,the gravity compensation method is researched,which improves accuracy and support for RNP.For constrained application scenarios,the relationship between model order and performance optimization is further analyzed,which provides a reference for the application of high-order spherical harmonic gravity model in engineering.The simulation results show that gravity compensation improves the horizontal positioning accuracy of 20 min pure inertial operation by 61%,and the cutting model can obtain 97%optimization of calculation efficiency while ensuring accuracy,which verifies its feasibility and effectiveness.

关 键 词：惯性基准系统 重力补偿 EGM2008球谐重力模型 所需导航性能 

分 类 号：V249.32[航空宇航科学与技术—飞行器设计]