Abstract
Aimed at characteristics of mass moment of missiles in exo-atmosphere, it’s inferred that 6-DOF mathematical model based on mass moment controlling stabilities on three axes. Considering the problem of harmoniously controlling two moving masses, moving mass based non-linear theorem was used to solve a series of problems met in attitude control system design. In order to weaken the chattering of the system, a saturation function is introduced to substitute for Sign function to improve the variable structure control law so that the chattering can be depressed. The simulation results illustrate the efficiency of this method.
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