Analysis Of Navigation Accuracy And Research Of Error Distribution Technology On Beyond Visual Rang Airborne Missile

In this paper the relative knowledge and the fundamental theory ofStrapdown inertial navigation system (SINS) are introduced.In the attitude updating algorithms research for SINS, It is discussedthat the quaternion algorithm and the equivalent rotation vector algorithm.The relation of the quaternion and the attitude matrix is analyzed, thesolution of the quaternion differential equation is given, the quaternioninitial value confirm and standardization disposal are introduced. Therotation vector differential equation is given. And we have also given anthree sample attitude algorithm based on rotation vector.In the velocity and position updating algorithms research for SINS,The sculling effect and the rotation effect in the velocity calculation isstudied and the sculling compensation two sample algorithms are derived.The scrolling effect and the rotation effect in the position calculation isstudied and the scrolling and rotation compensation two sample algorithmsare derived.In the error model research for SINS, the main error sources ofaffecting navigation accuracy are introduced. The reason of transferalignment on moving base is analyzed. The mathematical model of inertialsensor is given. Attitude error equation and velocity error equation andposition error equation are derived.The solution method of generating flight trajectory is given in detail.Then the simulating program is developed with MATLAB. The effectdegree of the different error sources on navigation accuracy is confirmedthrough the simulation. Then the different error is distributed suitably inorder to attain the SINS’s synthesis performance.