We propose a new approach to acceleration control of STT missiles which fully takes into account all nonlinearities of STT missiles, including the coupling effect due to bank and roll angles. We show that the missile dynamics with nonminimum phase can be transformed through a kind of partial linearization and singular perturbation techniques into the reduced system which is not only of minimum phase but also exactly I/O linearizable via feedback. Based on the resulting linear system, we can easily obtain a dynamic compensator which provides the desired input-output dynamic characteristics. We present a rigorous stability analysis of our autopilot controller and demonstrate the generality and practical use of our approach through simulation results. (Author) Page 1 Downloaded by KUNGLIGA TEKNISKA HOGSKOLEN KTH on July 30, 2015 | http://arc.aiaa.org | Abstract -In this paper, we propose a new approach to acceleration control of STT missiles, which takes into full account all nonlinearities of STT missiles including the coupling effect due to bank and roll angles. We show that the missile dynamics with nonminimum phase can be transformed through a kind of partial linearization and singular perturbation techniques into the reduced system which is not only of minimum phase but also exactly I/O linearizable via feedback. Based on the resulting linear system, we can easily obtain a dynamic compensator which provides the desired input-output dynamic characteristics. We present a rigorous stability analysis of our autopilot controller and demonstrate the generality and practical use of our approach through simulation results. (X, Y, Z) U,V,W p,g,r VM , M 7 m, p Q S, D
For homing guidance with a passive seeker, when we have a tractable object near a stationary target in case that the target itself can not be tracked, we propose a new guidance law named Squint Biased PNG. With both the invariant geometric information and the output of seeker squinting at the additional object, it is shown to be possible to guide vehicle to the aimed target. Some interpretations are made to get the proper engaging geometry for realistic limitations. And some important error configurations are investigated to prove the guidance performance.
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