Flight Control of Atmospheric Re-entry Vehicle with Non-linear Dynamic Inversion

2004 ◽  
Author(s):  
S. Juliana ◽  
Q.P. Chu ◽  
J.A. Mulder ◽  
T.J. van Baten
Keyword(s):  
Flight Control ◽  
Dynamic Inversion ◽  
Linear Dynamic ◽  
Non Linear

Supersonic transport aircraft longitudinal flight control law design

2004 ◽  
Vol 108 (1084) ◽  
pp. 319-329
Author(s):  
A. J. Steer
Keyword(s):  
Flight Control ◽  
Dynamic Inversion ◽  
Control Law ◽  
Transport Aircraft ◽  
Handling Qualities ◽  
Supersonic Transport ◽  
Linear Dynamic ◽  
Non Linear ◽  
Quality Design ◽  
Handling Quality

Abstract Modern civil transport aircraft utilise increasingly complex command and stability augmentation systems to restore stability, optimise aerodynamic performance and provide the pilot with the optimum handling qualities. Provided it has sufficient control power a second generation fly-by-wire supersonic transport aircraft should be capable of exhibiting similarly desirable low-speed handling qualities. However, successful flight control law design requires identification of the ideal command response type for a particular phase of flight, a set of valid handling quality design criteria and piloted simulation evaluation tasks and metrics. A non-linear mathematical model of the European supersonic transport aircraft has been synthesized on the final approach to land. Specific handling quality design criteria have been proposed to enable the non-linear dynamic inversion flight control laws to be designed, with piloted simulation used for validation. A pitch rate command system, with dynamics matched to the aircraft’s flight path response, will consistently provide Level 1 handling qualities. Nevertheless, pre-filtering the pilot’s input to provide a second order pitch rate response, using the author’s suggested revised constraints on the control anticipation parameter will generate the best handling qualities during the terminal phase of flight. The resulting pre-filter can be easily applied to non-linear dynamic inversion inner loop controllers and has simple and flight proven sensor requirements.

Design of Non-Linear Dynamic Inversion UAV with QFT

2012 ◽  
Vol 466-467 ◽  
pp. 676-679 ◽  
Author(s):  
Jie Li ◽  
Jie Zhang ◽  
Zhi Hui Xu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Inversion Method ◽  
Dynamic Inversion ◽  
Model Errors ◽  
Flight Control System ◽  
Linear Dynamic ◽  
Performance Requirements ◽  
Non Linear ◽  
Aerial Vehicle

Flight control system of UAV (Unmanned Aerial Vehicle) has limitations with non-linear dynamic inversion method. This paper introduces QFT based on non-linear dynamic inversion method, for avoiding model errors during existing non-linear function offset, QFT theory is presented firstly, then UAV model is established using non-linear dynamic inversion method, definituding the range of errors and system performance requirements, flight control system of UAV is designed with QFT, the simulating curves show that system has robustness stability.

scholarly journals A Comparison of Closed-Loop Performance of Multirotor Configurations Using Non-Linear Dynamic Inversion Control

Aerospace ◽  
2015 ◽  
Vol 2 (2) ◽  
pp. 325-352 ◽  
Author(s):  
Murray Ireland ◽  
Aldo Vargas ◽  
David Anderson
Keyword(s):  
Closed Loop ◽  
Dynamic Inversion ◽  
Linear Dynamic ◽  
Non Linear
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