Linear Analysis of Zero-Lift Pitching Moment Coefficient and Gravity Effects on Missile Autopilots

Date

2015-03-14

Author

Ovec, Naz T.
Erer, Koray S.
Kutay, Ali Türker

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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The most of the studies on disturbance rejection are covered with robust control methods, where this paper suggests a narrowed but a more simplified linear model based technique to assess the robustness of the controllers. In this paper presented, the problems originated from the disturbances are aimed to be obtained as far in advance as possible. The method used in this work reduces the iterative fine tuning time course between the non-linear simulation and the linear model; hence it enhances the authority over the design process and the designer's comprehension of the true linear model.

Subject Keywords

Acceleration, Aerodynamics, Control system synthesis, Iterative methods, Missile control, Nonlinear control systems, Robust control

URI

https://hdl.handle.net/11511/54980

Collections

Department of Aerospace Engineering, Conference / Seminar