HuChen_IMechE_Proc_I_221_I8.pdf (601.64 kB)
Model predictive control for non-linear missiles
The present paper reports an attempt of applying model predictive control (MPC)
to design an autopilot for a non-linear missile. The non-linear, fast dynamics of the missile
raise three issues in the design of an MPC algorithm: the choice of the MPC performance
index, in particular the terminal weighting term, to compromise the performance and the
stability requirements; loss of the global minimum in the online optimization since it is a nonlinear
optimization; and the computational time limitation imposed by the fast sampling
requirement. For the first issue, a procedure is developed to determine the terminal weighting
term using a new representation of the control sequence in the moving horizon. For the other
two issues, a new initial control profile and an associated control strategy are adopted in each
optimization routine. It is shown that the new MPC algorithm can guarantee stability, even
when a local minimum is attained in the online optimization or the optimization process has
to stop owing to the limitation of the sampling time. Simulation results carried on the missile
show that good performance and stability are achieved by the new MPC algorithm, whereas
four other current MPC algorithms lose their stability.
History
School
- Aeronautical, Automotive, Chemical and Materials Engineering
Department
- Aeronautical and Automotive Engineering
Citation
HU, X-B. and CHEN, W-H., 2007. Model predictive control for non-linear missiles. Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering, 221 (8), pp. 1077-1089 [DOI: 10.1243/09596518JSCE394]Publisher
© IMechE / Professional Engineering PublishingPublication date
2007Notes
This journal article was published in the journal, Proceedings of the Institution of Mechanical Engineers, Part I [© IMechE] and is also available at: http://journals.pepublishing.com/content/119778ISSN
0959-6518Language
- en