A four-sample coning compensation for the modern SINS attitude algorithm is simulated in the digital signal processor under the condition of swaying motion, and compared with a three-sample coning compensation, an three-sample equivalent rotation vector, and an sample Peano-Baker approach.

Research of SINS Moving Base Transfer Alignment Based on Hybrid Annealed Particle Filter;

Design and simulation on SINS self-alignment for carrier born aircraft;

Research on Measurement Error of the SINS s Accelerator;

The results indicate that this method can effectively achieve the initial alignment of the strapdown inertial navigation system and the method can not only satisfy the alignment precision,but also greatly reduce the alignment time compared with the traditional method.

Using Eulerian angle information in rudder-control-loop is a general method in the strapdown inertial navigation system(SINS) of aerocraft.

Based on error analysis, the influence of error sources on strapdown inertial navigation systems is discussed.

The angular velocity was computed using accelerometers instead of angular velocity gyroscopes in gyroscope-free strap-down inertial navigation system(GFSINS).

The advanced simulation system platform RT-LAB and software MATLAB/Simulink are expounded,the Runge-Kutta integrator models is designed,and strap-down inertial navigation simulation models based on MATLAB/Simulink is built.

According to the require of data Acquisition and data Processor in the strap-down inertial navigation system,this paper presents a new hardware scheme of navigation computer system that uses high performance DSP as core and FPGA as mainly external I/O interface.