Finally, the positioning error model is verified by the information of the star obtained from the optical measurement device in range and the device whose location are known. And then, based on the positioning error model we analyze and simulate the positioning error which are caused by the error of the star tracking platform with the MATLAB software. Based on these we built the positioning error model of the celestial navigation. By building the mathematical model of the airborne celestial navigation system based on the inertial navigation system, using the method of linear coordinate transformation, we establish the error transfer equation for the positioning algorithm of airborne celestial system. Thus the navigation accuracy of airborne celestial navigation subsystem directly decides the accuracy of the integrated navigation system if it works for long time. Zheng, Xiaoqiang Deng, Xiaoguo Yang, Xiaoxu Dong, QiangĬelestial navigation subsystem of airborne celestial/ inertial integrated navigation system periodically correct the positioning error and heading drift of the inertial navigation system, by which the inertial navigation system can greatly improve the accuracy of long-endurance navigation. Research on the error model of airborne celestial/ inertial integrated navigation system Optimal scheme of star observation of missile-borne inertial navigation system/stellar refraction integrated navigation. The simulation results indicated that the proposed observation scheme has an accurate positioning performance, and the results of EKF and UKF are similar. The results of the Extended Kalman Filter (EKF) and Unscented Kalman Filter (UKF) are compared and impact factors of navigation accuracy are studied in the simulation. To verify the feasibility of the proposed scheme, numerical simulation is conducted. Based on the condition when PDOP reaches the minimum value, an optimized observation scheme is proposed. Position Dilution of Precision (PDOP) for stellar refraction is introduced and the corresponding equation is derived. In this study, a missile-borne inertial/stellar refraction integrated navigation scheme is proposed. To achieve accurate and completely autonomous navigation for spacecraft, inertial/celestial integrated navigation gets increasing attention. Optimal scheme of star observation of missile-borne inertial navigation system/stellar refraction integrated navigation An inertial navigator and reference system based on this approach would probably have both fewer components and simpler algorithms, due to the obviation of the first level of integration in classic inertial navigators. Velocimeters of this type would obviate the use of both gyros and accelerometers, and allow inertial navigation to be conducted together with vehicle attitude control, through the derivation of rotation rates from the ratios of the three possible velocimeter pairs. The Kennedy-Thorndike (1932) experiment points to the feasibility of fiber-optic inertial velocimeters, to which state-of-the-art technology could furnish substantial sensitivity and accuracy improvements. Inertial navigation without accelerometers
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |