An adaptive pitch axis autopilot design procedure is presented. The
design procedure is applicable to both stable and unstable pitch axis models
and to those having nonminimum phase. The design approach assumes
the adaptive autopilot is activated after achieving level flight. It is shown a
rate-feedback compensator can be designed to ensure stable level flight
pitch axis operation for the entire desired flight regime. The adaptive
control loop design utilizes a pole-placement algorithm. The closed-loop
characteristic polynomial is designed to have dominant poles of that of an
ideal second order system to obtain the desired transient response. The
identification of the system uses a modified least-squares algorithm with a
variable forgetting factor. The nonlinear pitch axis model is used in
simulations to evaluate the design. Command response tests include the
step response and the ramp command response.
Simulation results indicate that the adaptive pitch axis autopilot is
capable of tracking altitude commands after activation. The closed-loop
system response is close to that of the ideal second order system having the
dominant poles. / Graduation date: 1991
| Identifer | oai:union.ndltd.org:ORGSU/oai:ir.library.oregonstate.edu:1957/38014 |
| Date | 14 June 1990 |
| Creators | Chen, Long Ren |
| Contributors | Saugen, John L. |
| Source Sets | Oregon State University |
| Language | en_US |
| Detected Language | English |
| Type | Thesis/Dissertation |
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