弹载大视场星惯组合深度融合导航技术

为了降低弹载星惯组合（Stellar-INS）飞行中段对调姿观星的要求，提高星惯组合姿态精度，提出了大视场（LFOV）星惯组合深度融合导航方法。小视场（NFOV）星敏感器输出星矢量为主，大视场星敏感器可同时输出姿态和星矢量信息，分别推导了基于星敏感器输出姿态和星矢量信息的观测方程，分析了星矢量和姿态观测方法之间的关联性。建立了包含星惯安装误差、陀螺误差以及初始平台误差角的星惯组合全误差项模型，基于线性卡尔曼滤波给出了深度融合导航方法。开展了数学仿真验证，分析了不同调姿观星路径约束下，大/小视场星惯组合性能差异。结果表明，大视场星惯组合深度融合导航方法不仅可以降低调姿观星约束要求，还可以实现组合姿态性能提升。

Deep fusion navigation technology of missile-borne Stellar-INS with LFOV

To lower the requirement for attitude adjustment and star observation in the middle stage of missile-borne Stellar-Inertial Navigation System (Stellar-INS) combination flight, and to improve the accuracy of the Stellar-INS attitude, this paper proposes a deep fusion navigation method for the Stellar-INS with Large Field of View (LFOV) star sensors. The Narrow Field of View (NFOV) star sensor outputs the star vector, while the LFOV star sensor can output both the attitude and the star vector information. The observation equations based on the output attitude and the star vector information from the star sensors are derived, respectively, and the correlation of the Stellar/INS combined method with the LFOV/NFOV is analyzed. Considering the Stellar-INS installation error, gyro error and initial platform error angle, this study establishes a total error term model of the Stellar-INS, and proposes a deep fusion navigation method using the linear Kalman filter. Finally, different performance of the LFOV/NFOV is analyzed via mathematical simulation under the constraint of different attitude observation paths. The results show that the deep fusion navigation method for the Stellar-INS with the LFOV star sensor can not only reduce the constraint requirements for attitude adjustment and observation, but also improve the performance of the combined attitude.