An Optimal Estimation of Aerodynamic Parameters for GPS Guided Missile

Abstract:

The disturbance factors in the missile flight are obvious,so the analytical equations of missile longitudinal disturbance of movement is derived . The missile body longitudinal aerodynamic parameters are fitting out with wind tunnel experimental data. The equation of system state takes the aerodynamic coefficient errors interference source and GPS error sources as the state variables, and the system measurement equation adopts GPS pseudo-range measurements. In passive segment, the aerodynamic coefficients disturbing errors sources of th missile longitudinal plane is estimated optimally with extended Kalman filter. The results show that the method accelerate the convergence speed of the disturbance source errors, and improve the estimation accuracy of the perturbation errors.

• Periodical: Applied Mechanics and Materials (Volumes 325-326)
• Pages: 734-737
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.325-326.734
• Online since: June 2013
• Authors: Li Yan, Chen Yang, Chuan Bing Ding
• Keywords: Disturbance Source, GPS Pseudo-Range, Kalman Filter (KF), Longitudinal Movement, Missile, Optimal Estimation

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