Nonlinear inversion flight control for a supermaneuverable aircraft

Snell, S. A.; Enns, Dale; Garrard, William L.

doi:10.2514/3.20932

Cited by 496 publications

(144 citation statements)

References 10 publications

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“…In [5], the original nonlinear dynamic system is transformed into a linear system by coordinate transformation and state feedback. In [7], a generalised dynamic inversion control was proposed to track angle of attack, side-slip angle and roll angle.…”

Section: Introductionmentioning

confidence: 99%

Adaptive fuzzy multi‐surface sliding control of multiple‐input and multiple‐output autonomous flight systems

Norton

Khoo

Kouzani

et al. 2015

IET Control Theory & Applications

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In this study, we proposed an adaptive fuzzy multi-surface sliding control (AFMSSC) for trajectory tracking of 6 degrees of freedom inertia coupled aerial vehicles with multiple inputs and multiple outputs (MIMO). It is shown that an adaptive fuzzy logic-based function approximator can be used to estimate the system uncertainties and an iterative multisurface sliding control design can be carried out to control flight. Using AFMSSC on MIMO autonomous flight systems creates confluent control that can account for both matched and mismatched uncertainties, system disturbances and excitation in internal dynamics. It is proved that the AFMSSC system guarantees asymptotic output tracking and ultimate uniform boundedness of the tracking error. Simulation results are presented to validate the analysis.

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Section: Introductionmentioning

confidence: 99%

Adaptive fuzzy multi‐surface sliding control of multiple‐input and multiple‐output autonomous flight systems

Norton

Khoo

Kouzani

et al. 2015

IET Control Theory & Applications

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“…Control surface deflections are finally obtained from these moments using some control allocation algorithm. This two time scale approach along with the reasonable assumption that the control surfaces only generate moments without producing any appreciable force, help avoid the occurrence of internal dynamics, whose stability is the main challenge in the NDI algorithm 5,8,15 . Let us first design the control for simulation implementation of Herbst manoeuver under the nominal condition i.e., no CG variation.…”

Section: Control Design For Herbstmentioning

confidence: 99%

“…Such extreme conditions call for use of nonlinear control techniques as gain scheduled linear controls become ineffective. Nonlinear dynamic inversion (NDI) or feedback linearising control is a popular nonlinear control design technique which has been applied to flight control problems by various researchers [5][6][7][8] . The basic underlying idea of this method is to first choose linear asymptotically stable error dynamics and then replace the system dynamics in it and solve for the control input.…”

Section: Control Design For Herbstmentioning

confidence: 99%

“…From Eqn. (33) final control surface deflections can be computed using the matrix pseudo inverse method of control allocation as outlined in the literature 5 .…”

Section: Control Design For Herbstmentioning

confidence: 99%

“…Moreover, some researchers [2][3][4] have considered only the linearised model of the asymmetric dynamics for closed loop control design purposes as some simple flight objective such as steady wings level trim was considered. Various nonlinear control methods such as the dynamic inversion or the sliding mode have been applied without considering the lateral CG variation effects by various researchers over the past two decades [5][6][7][8][9] . However, dynamic inversion based nonlinear control design for a combat aircraft performing some demanding post stall manoeuvers such as the Herbst with such laterally asymmetric CG location, as addressed in this paper, is a completely novel attempt.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Dynamic Inversion Control for Performing Herbst Manoeuver with Lateral Center-of-Gravity Offset

Mukherjee

Sinha

2017

Def. Sc. Jl.

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The present study addresses the effects of lateral center-of-gravity (CG) movement, resulting from asymmetric firing of some of the onboard stores, on the dynamics and control of a combat aircraft while attempting the highly demanding Herbst manoeuver. The complete six degree-of-freedom equations of motion of the aircraft for such lateral CG offset are derived in two different body reference frames attached either to the symmetric nominal CG location or to the shifted asymmetric CG location. The Herbst manoeuver is first simulated using nonlinear dynamic inversion based control to handle the highly nonlinear post stall flight dynamics considering the standard equation of motion without considering any lateral CG variation. Thereafter, it is observed that if the same controller is retained, the manoeuver performance deteriorates significantly even when the CG undergoes a moderate lateral shift. To overcome this shortfall, closed loop controllers are next designed incorporating both the models of asymmetric dynamics as derived in this paper. It is validated through MATLAB simulations that both the controls, thus designed, can recover the original manoeuver performance almost completely; however, the first one requires more complex computations and hence increased computation time while the second one requires that all the measurements be transformed to the new body reference frame at every time step.

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Input-output invertibility and sliding mode control for close formation flying of multiple UAVs

Singh

Pachter

Chandler

et al. 2000

Int. J. Robust Nonlinear Control

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Nonlinear inversion flight control for a supermaneuverable aircraft

Cited by 496 publications

References 10 publications

Adaptive fuzzy multi‐surface sliding control of multiple‐input and multiple‐output autonomous flight systems

Adaptive fuzzy multi‐surface sliding control of multiple‐input and multiple‐output autonomous flight systems

Dynamic Inversion Control for Performing Herbst Manoeuver with Lateral Center-of-Gravity Offset

Input-output invertibility and sliding mode control for close formation flying of multiple UAVs

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