Nonlinear dynamics and SDRE control applied to a high-performance aircraft in a longitudinal flight considering atmospheric turbulence in flight

Santos, Guilherme Pacheco dos; Balthazar, José Manoel; Janzen, Frederic Conrad; Rocha, Rodrigo Tumolin; Nabarrete, Airton; Tusset, Ângelo Marcelo

doi:10.1016/j.jsv.2018.08.021

Cited by 10 publications

(5 citation statements)

References 14 publications

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“…Still with [9], is presented an autopilot project using loop modeling H∞ for missiles with high attack angles. Finally, as addressed by [10], performing the nonlinear control project considering the longitudinal dynamics of a high-performance aircraft.…”

Section: Article History Received 03 May 2021 Revised 24 May 2021 Accepted 26 May 2021mentioning

confidence: 99%

“…The basic equations of longitudinal movement are represented in the system (1), where the drag was considered small enough to be disregarded compared to the thrust and weight [10].…”

Section: Mathematical Model For Longitudinal Flight Of the F-8 Crusader Aircraftmentioning

confidence: 99%

“…Fig. 2 shows the vector representation of the velocity components , and along the , and axes [10].…”

Section: { (̇+mentioning

confidence: 99%

“…where the aircraft lift forces represented by and can be obtained using the following equations [5,10]…”

Section: { (̇+mentioning

confidence: 99%

“…2. Velocity componentsConsidering Fig.2, one can define the following mathematical speed ratios[10] as { = taṅ =̇tan +̇sec2 (2)Replacing (2) in (1), one obtains…”

mentioning

confidence: 99%

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SDRE and LQR Controls Comparison Applied in High-Performance Aircraft in a Longitudinal Flight

Santos

Kossoski

Balthazar

et al. 2021

IJRCS

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This paper presents the design of the LQR (Linear Quadratic Regulator) and SDRE (State-Dependent Riccati Equation) controllers for the flight control of the F-8 Crusader aircraft considering the nonlinear model of longitudinal movement of the aircraft. Numerical results and analysis demonstrate that the designed controllers can lead to significant improvements in the aircraft's performance, ensuring stability in a large range of attack angle situations. When applied in flight conditions with an angle of attack above the stall situation and influenced by the gust model, it was demonstrated that the LQR and SDRE controllers were able to smooth the flight response maintaining conditions in balance for an angle of attack up to 56% above stall angle. However, for even more difficult situations, with angles of attack up to 76% above the stall angle, only the SDRE controller proved to be efficient and reliable in recovering the aircraft to its stable flight configuration.

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Section: Article History Received 03 May 2021 Revised 24 May 2021 Accepted 26 May 2021mentioning

confidence: 99%

“…The basic equations of longitudinal movement are represented in the system (1), where the drag was considered small enough to be disregarded compared to the thrust and weight [10].…”

Section: Mathematical Model For Longitudinal Flight Of the F-8 Crusader Aircraftmentioning

confidence: 99%

“…Fig. 2 shows the vector representation of the velocity components , and along the , and axes [10].…”

Section: { (̇+mentioning

confidence: 99%

“…where the aircraft lift forces represented by and can be obtained using the following equations [5,10]…”

Section: { (̇+mentioning

confidence: 99%

“…2. Velocity componentsConsidering Fig.2, one can define the following mathematical speed ratios[10] as { = taṅ =̇tan +̇sec2 (2)Replacing (2) in (1), one obtains…”

mentioning

confidence: 99%

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SDRE and LQR Controls Comparison Applied in High-Performance Aircraft in a Longitudinal Flight

Santos

Kossoski

Balthazar

et al. 2021

IJRCS

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Optimal control of nonlinear aeroelastic system with non‐semi‐simple eigenvalues at Hopf bifurcation points

Wang

Chen

Pei

et al. 2020

Optim Control Appl Methods

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This study discusses an efficient method of the Hopf bifurcation control for nonlinear aeroelastic system. The nonlinear aeroelastic system whose linear part has multiple non‐semi‐simple eigenvalues at critical point gives rise to Hopf bifurcations. The method of the multiple scales and the well‐known linear quadratic regulator method are used to deal with the optimal control of the nonlinear system at Hopf bifurcation points. The modal optimal control equation and modal Riccati equation of the nonlinear system are developed to simplify the computations. The conventional Potter's algorithm is extended to solve modal Riccati equation for the modal Riccati matrix of the Hopf bifurcation control. The first‐order approximation solutions are developed, which include the gain vectors and inputs. By the way of optimal control, the admissible control input and trajectory of the linear part of the nonlinear aeroelastic system are obtained to minimize the performance measure. Then, we set the appropriate first‐order gain vector to adjust the convergence speed of this nonlinear system.

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Dynamical Analysis and Control of Parametric Surface Waves in a Nonlinear and Non-ideally Excited Tank

Gonçalves,

Balthazar,

Jarzȩbowska

et al. 2024

Springer Proceedings in Mathematics &Amp; Statistics

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Nonlinear dynamics and SDRE control applied to a high-performance aircraft in a longitudinal flight considering atmospheric turbulence in flight

Cited by 10 publications

References 14 publications

SDRE and LQR Controls Comparison Applied in High-Performance Aircraft in a Longitudinal Flight

SDRE and LQR Controls Comparison Applied in High-Performance Aircraft in a Longitudinal Flight

Optimal control of nonlinear aeroelastic system with non‐semi‐simple eigenvalues at Hopf bifurcation points

Dynamical Analysis and Control of Parametric Surface Waves in a Nonlinear and Non-ideally Excited Tank

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