SINS/GPS组合导航半实物仿真系统设计

SINS/GPS组合导航具有精度高、抗干扰性好等优点,被广泛应用于各个领域,通常采用半实物仿真的方法检测其性能。针对由于仿真系统参试设备多、设备接口复杂、数据传输量大而导致的仿真实时性难以保证的问题,提出了一种基于光纤网络的半实物仿真方法,利用光纤网络虚拟共享内存的特点,对系统的各设备进行统一管理,保障了系统的实时性。系统的仿真应用和试验结果表明,半实物仿真系统设计合理,具有良好的人机交互能力、数据处理能力和异常状态处理能力。该仿真系统具有良好的通用性和可扩展性,具有一定的推广使用价值。

Novel scheme of high precision inertial measurement for high-speed rotating carriers

In order to satisfy the requirement of high precision measurement in a high dynamic environment, a kind of gyro aided multi-accelerometer inertial measurement unit （GAMA-IMU） with six accelerometers and two gyros （6A2G） was proposed in this paper. The available configurations have the problem of low measurement precision In a high dynamic environment due to channel coupling. The three channels were decoupled when calculating the angular velocity in the proposed configuration. The yawing and pitching angular velocity were directly measured by gyros, while only the rolling angular velocity was obtained by the GAMA-IMU indirectly from the rolling angular acceleration and quadratic component of rolling angular velocity. Then a single channel rolling angular velocity calculation model was established and the extended Kalman filter （EKF） was used to do state esti- mation. Simulations were carried out and results indicated that the calculation precision of the proposed 6A2G configuration could meet the demand of high precision measurement for a high-speed rotating carrier.

INS/CNS/GNSS机载高性能空中对准技术研究

为提升机载惯导空中对准精度、缩短对准时间,提出了一种基于广义序贯滤波的卫星天文辅助高性能空中对准方法。广义序贯滤波用来解决因卫星导航系统与天文导航系统输出频率不同带来的异步信息融合问题,同时增强了算法可重构性,在天文信息不可用时依然可利用卫星信息完成对准。整个对准过程分为两个阶段:一是卫星辅助大失准角修正阶段,用时90s;二是卫星天文辅助精对准阶段,用时30s。在真实飞行轨迹条件下对该算法进行了验证,结果表明:对准时间可缩短为2min,同时航向角对准精度可提升到0.004°,所提空中对准方法在很大程度上提升了武器装备的快速反应能力和精确打击能力,具有一定的工程意义。