CAJ | 학술논문

本文通过仿真实验，研究了基于星敏感器的天文/惯导组合导航系统的导航性能和特点。首先分析了天文导航的基本原理，并给出了天文/惯导组合导航算法的理论模型。在此基础上，建立了天文导航和捷联惯性导航的仿真模型，实现了天文/惯导组合导航系统仿真。仿真结果表明：基于星敏感器的天文/惯导组合导航能够有效抑制惯导的长时漂移累积误差，有利于实现机载远程长航时的高精度导航。
본문통과방진실험，연구료기우성민감기적천문/관도조합도항계통적도항성능화특점。수선분석료천문도항적기본원리，병급출료천문/관도조합도항산법적이론모형。재차기출상，건립료천문도항화첩련관성도항적방진모형，실현료천문/관도조합도항계통방진。방진결과표명：기우성민감기적천문/관도조합도항능구유효억제관도적장시표이루적오차，유리우실현궤재원정장항시적고정도도항。
According to the simulation experiments, the performance and characteristic of CNS/INS integrated navigation are analyzed in this paper. Firstly, the basic theory of celestial navigation is discussed, and the algorithm of CNS/INS integrated navigation is presented. Then, the celestial navigation and inertial navigation simulation models are set up. What’s more, the CNS/INS integrated navigation simulation system is realized. The simulation results show that the accumulative errors of inertial navigation are checked effectively by the CNS/INS integrated navigation, which is benefit to realize the high precision airborne navigation with long-distance and long-endurance.