An integrated approach to flight control design using dynamic inversion and μ-synthesis

1993 ◽  
Author(s):  
Richard J. Adams ◽  
Siva S. Banda
Keyword(s):  
Flight Control ◽  
Control Design ◽  
Integrated Approach ◽  
Dynamic Inversion

Nonlinear Dynamic Inversion Flight Control Design for Guided Projectiles

2020 ◽  
Vol 43 (5) ◽  
pp. 975-980
Author(s):  
Steven Tipàn ◽  
Spilios Theodoulis ◽  
Sovanna Thai ◽  
Michael Proff
Keyword(s):  
Flight Control ◽  
Nonlinear Dynamic ◽  
Control Design ◽  
Dynamic Inversion ◽  
Nonlinear Dynamic Inversion

Stochastic Approach to Robust Flight Control Design Using Hierarchy-Structured Dynamic Inversion

2011 ◽  
Vol 34 (5) ◽  
pp. 1573-1576 ◽  
Author(s):  
Jun'ichiro Kawaguchi ◽  
Tetsujiro Ninomiya ◽  
Yoshikazu Miyazawa
Keyword(s):  
Flight Control ◽  
Control Design ◽  
Stochastic Approach ◽  
Dynamic Inversion ◽  
Robust Flight Control

Flight control design using robust dynamic inversion and time-scale separation

Automatica ◽  
1996 ◽  
Vol 32 (11) ◽  
pp. 1493-1504 ◽  
Author(s):  
Jacob Reiner ◽  
Gary J. Balas ◽  
William L. Garrard
Keyword(s):  
Flight Control ◽  
Time Scale ◽  
Control Design ◽  
Dynamic Inversion ◽  
Scale Separation ◽  
Time Scale Separation

Flight control design with hierarchical dynamic inversion

2010 ◽  
Author(s):  
Kemao Peng ◽  
Kai Yew Lum ◽  
Ben M Chen
Keyword(s):  
Flight Control ◽  
Control Design ◽  
Dynamic Inversion

scholarly journals Non-Linear Dynamic Inversion Control Design for Rotorcraft

Aerospace ◽  
2019 ◽  
Vol 6 (3) ◽  
pp. 38 ◽  
Author(s):  
Joseph Horn
Keyword(s):  
Flight Control ◽  
State Feedback ◽  
Control Design ◽  
Linear Analysis ◽  
Order System ◽  
Dynamic Inversion ◽  
Order Linear ◽  
Full State ◽  
Non Linear ◽  
Full State Feedback

Flight control design for rotorcraft is challenging due to high-order dynamics, cross-coupling effects, and inherent instability of the flight dynamics. Dynamic inversion design offers a desirable solution to rotorcraft flight control as it effectively decouples the plant model and effectively handles non-linearity. However, the method has limitations for rotorcraft due to the requirement for full-state feedback and issues with non-minimum phase zeros. A control design study is performed using dynamic inversion with reduced order models of the rotorcraft dynamics, which alleviates the full-state feedback requirement. The design is analyzed using full order linear analysis and non-linear simulations of a utility helicopter. Simulation results show desired command tracking when the controller is applied to the full-order system. Classical stability margin analysis is used to achieve desired tradeoffs in robust stability and disturbance rejection. Results indicate the feasibility of applying dynamic inversion to rotorcraft control design, as long as full order linear analysis is applied to ensure stability and adequate modelling of low-frequency dynamics.

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