In this thesis, autopilots are developed for missiles with moderate dynamics and
stationary targets. The aim is to use the designs in real applications. Since the real
missile model is nonlinear, a linearization process is required to get use of systematic
linear controller design techniques. In the scope of this thesis, the linear quadratic
full state feedback approach is applied for developing missile autopilots. However,
the limitations of measurement systems on the missiles restrict the availability of all
the states required for feedback. Because of this fact, the linear quadratic design will
be approximated by the use of projective control theory. This method enables the
designer to use preferably static feedback or if necessary a controller plus a low
order compensator combination to approximate the full state feedback reference.
Autopilots are checked for the validity of linearization, robust stability against
aerodynamic, mechanical and measurement uncertainties.
| Identifer | oai:union.ndltd.org:METU/oai:etd.lib.metu.edu.tr:http://etd.lib.metu.edu.tr/upload/4/1089929/index.pdf |
| Date | 01 January 2003 |
| Creators | Doruk, Resat Ozgur |
| Contributors | Kocaoglan, Erol |
| Publisher | METU |
| Source Sets | Middle East Technical Univ. |
| Language | English |
| Detected Language | English |
| Type | M.S. Thesis |
| Format | text/pdf |
| Rights | To liberate the content for public access |
Page generated in 0.0018 seconds