Experimental Validation of an Adaptive Total Energy Control System Strategy for the Longitudinal Dynamics of a Fixed-Wing Aircraft

Brigido-González, J D; Rodriguez-Cortes, H.

doi:10.1061/(asce)as.1943-5525.0000512

Cited by 14 publications

(6 citation statements)

References 20 publications

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“…The simulation also implements the aircraft longitudinal controller developed in Brigido-González and Rodríguez-Cortés 23 to command V¯,α¯, and θ¯ to constant references. The simulation consists of the following steps.…”

Section: Simulations Resultsmentioning

confidence: 99%

“…The stability properties of the equilibrium point can be characterized by the locations of the eigenvalues of the linear approximation of equation 22about equation 23. 20 The first step is to verify that the closed-loop dynamics has an equilibrium point at (23).…”

Section: Closed-loop Stability Analysismentioning

confidence: 99%

“…The set of equations in (27) can be arranged in matrix form, assuming that s % as follows thus, to ensure that the equilibrium point is unique and equal to equation (23) the control gains k , k a i , and k r i must be adequately selected. In a small neighborhood of the equilibrium point (equation 23), the closed-loop dynamics can be approximated by its linearization about equation (23). The linear approximation of equation 22can be expressed as ; 6 6 6 6 6 6 6 6 6 6 6 4 3 7 7 7 7 7 7 7 7 7 7 7 5 and…”

Section: Closed-loop Stability Analysismentioning

confidence: 99%

See 2 more Smart Citations

A coordinated turn controller for a fixed-wing aircraft

Corona-Sánchez

Caso

Rodriguez-Cortes

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper describes the design of a controller for a fixed-wing aircraft to make it perform coordinated turns. First, a state feedback partial linearization controller drives the airplane to carry out an ideal coordinated turn. A second control loop, inspired by the total heading control system technique, mixes the ailerons and rudder inputs to perform a coordinated turn considering the sideslip dynamics. The control design development gives new insights to establish the fundamental basis for the total heading control system. Simulations in an advanced flight simulator (X-Plane 10) are presented to show the closed-loop system behavior.

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Section: Simulations Resultsmentioning

confidence: 99%

Section: Closed-loop Stability Analysismentioning

confidence: 99%

Section: Closed-loop Stability Analysismentioning

confidence: 99%

See 1 more Smart Citation

A coordinated turn controller for a fixed-wing aircraft

Corona-Sánchez

Caso

Rodriguez-Cortes

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…TECS was chosen for its ability to decouple altitude and speed responses, without the need to employ a more accurate model of the aircraft. For maneuvers such as landing, this decoupling is important because in this maneuver the aircraft must control the longitudinal position while avoiding perturbations in altitude [15]. TECS uses a MIMO (multiple-input multiple-output) control algorithm to provide operational and performance strength in the most complete way in all operational modes and flight conditions.…”

Section: Introductionmentioning

confidence: 99%

Experimental Validation of Total Energy Control System for UAVs

et al. 2019

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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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“…In [17], TECS control action is interpreted in terms of the kinetic and potential energy management that pilots do when flying a plane. Recently, references [18] and [19] proposed nonlinear versions of TECS, and reference [20] employed the TECS method to solve the trajectory tracking problem for quadrotors. The total energy rate, which is proportional to the time derivative of the Hamiltonian function, is the basis for the synthesis of the TECS controller.…”

Section: Introductionmentioning

confidence: 99%

A Total Energy Attitude Control System Strategy for Rigid Spacecraft

Cortés-Martínez

Rodriguez-Cortes

2019

IEEE Access

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This paper aims to design a controller based on the Total Energy Control System (TECS) method, to solve the attitude trajectory tracking problem for rigid spacecraft. TECS objective is to command the total energy rate using a proportional-integral (PI) controller. The attitude control objective fixes the total energy rate objective. The spacecraft attitude is represented directly in the manifold of the Special Orthogonal Group SO(3). Ultimate boundedness of the closed-loop trajectories is concluded using Lyapunov theory. The second objective of this paper is to test the attitude controller through real-time experiments, employing a testbed based on an underwater prototype with neutral buoyancy that can rotate unrestricted around the three axes.INDEX TERMS Attitude control, Hamiltonian dynamics, Lyapunov theory, real-time control.

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Experimental Validation of an Adaptive Total Energy Control System Strategy for the Longitudinal Dynamics of a Fixed-Wing Aircraft

Cited by 14 publications

References 20 publications

A coordinated turn controller for a fixed-wing aircraft

A coordinated turn controller for a fixed-wing aircraft

Experimental Validation of Total Energy Control System for UAVs

A Total Energy Attitude Control System Strategy for Rigid Spacecraft

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