High performance strapdown inertial navigation system algorithms for space flight

To satisfy inertial navigation demands for space flight, high performance space-oriented strapdown inertial navigation system (SINS) algorithms are developed in the paper. The new algorithms are derived from a two-speed updating approach, which are far fit for the integration in digital computer than conventional methods and improve the robustness of space inertial navigation system (INS) in high dynamic environments. The performance is validated through high-fidelity simulations, and inertial measurements data for simulating are generated based on true trajectories of space vehicles and inertial sensor (gyro and accelerometer) error models. Moreover, the effects of inertial sensorspsila measurement errors on the precision of the new spaceflight SINS algorithms are evaluated.