Flight Testing TECS — The Total Energy Control System

1986 ◽  
Author(s):  
James R. Kelly ◽  
Lee H. Person ◽  
Kevin R. Bruce
Keyword(s):  
Control System ◽  
Total Energy ◽  
Flight Testing ◽  
Energy Control

Total Energy Control System for Helicopter Flight/Propulsion Integrated Controller Design

2007 ◽  
Vol 30 (4) ◽  
pp. 1030-1039 ◽  
Author(s):  
Sheng-Wen Chen ◽  
Pang-Chia Chen ◽  
Ciann-Dong Yang ◽  
Yaug-Fea Jeng
Keyword(s):  
Control System ◽  
Total Energy ◽  
Controller Design ◽  
Energy Control ◽  
Helicopter Flight ◽  
Integrated Controller

Integration of four-dimensional guidance with total energy control system

1991 ◽  
Vol 14 (3) ◽  
pp. 564-573 ◽  
Author(s):  
Isaac Kaminer ◽  
Patrick O'Shaughnessy
Keyword(s):  
Control System ◽  
Total Energy ◽  
Energy Control

scholarly journals Experimental Validation of Total Energy Control System for UAVs

Energies ◽  
2019 ◽  
Vol 13 (1) ◽  
pp. 14 ◽  
Author(s):  
Pedro Jimenez ◽  
Piotr Lichota ◽  
Daniel Agudelo ◽  
Krzysztof Rogowski
Keyword(s):  
Control System ◽  
Total Energy ◽  
Inertial Sensor ◽  
Low Cost ◽  
Linear Acceleration ◽  
Scale Model ◽  
Model Parameters ◽  
Design Development ◽  
State Equations ◽  
Energy Control

This paper presents an analysis of a Total Energy Control System (TECS) introduced by Lambregts to control unmanned aerial vehicle (UAV) velocity and altitude by using the total energy distribution. Furthermore, an extended Kalman filter (EKF) approach was used to predict aircraft response in terms of angular rates and linear acceleration during a test flight campaign. From both approaches, state equations were obtained to model the aircraft using Matlab-Simulink. From an aerodynamic study, airplane characteristics were obtained in terms of non-dimensional derivatives and compared to those obtained from the experimental methods. It was determined that TECS approach was very accurate; however, disturbance errors could be decreased by adjusting some model parameters. On the other hand, it was difficult to obtain a real estimation from the EKF method due to the presence of turbulence during flight and the relatively low inertia of the scale model. Dynamic characteristics were validated using a low-cost inertial sensor that cab be easily integrated in UAV platforms. The gathered data can be used to predict model characteristics by integrating the information into flight simulators for future design development.

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