9th International Conference on Recent Advances in Space Technologies (RAST), İstanbul, Turkey, 11 - 14 June 2019, pp.919-925
Linear quadratic one-sided optimized guidance laws and particle swarm optimization guidance law are investigated for hypervelocity asteroid intercept mission. Also, this paper examines the effect of noise on the line of sight measurements. In order to extract the actual value of the line of sight rate, the Kalman filter algorithm is used for certain guidance laws. Homing loop simulation results based upon Monte Carlo method show the effectiveness and accuracy of the various guidance laws.