Design of an autoland controller for a carrier-based F-14 aircraft using H/sub ∞/ output-feedback synthesis

Niewoehner, Robert; Kaminer, Isaac

doi:10.1109/acc.1994.735009

Cited by 18 publications

(10 citation statements)

References 4 publications

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“…This model was verified by comparison with the nominal-state matrices ({ = [l, lf) obtained from the linearization of the nonlinear model described in Ref. 18. Furthermore, observe that the inertia-<¥ matrix Im is a function of ( 1 and, therefore, aircraft-state and input matrices depend nonlinearly on s 1 • However, the impact of reduced s 1 on Im was negligible.…”

Section: Niewoehner and Kaminermentioning

confidence: 73%

“…-Yopy (17) where CMo is the nominal aircraft pitching moment, TcJ is the trim thrust setting, Py is the engine's moment arm, qmax is the maximum pitch-rate requirement, and stabmax represents a maximum stabilator deflection in the appropriate direction. Equation ( 17) is affine in CL"ab" To ensure sufficient stabilator authority to provide qmax the pitch-rate maneuverability requirement can be posed as the following LMI: (18) where + lstah C L"ab(nnminal) stabmax) Similar arguments can be used to obtain constraints on other angular rates. Constraint (18) …”

Section: Including Maneuverability Requirementsmentioning

confidence: 99%

“…Equation ( 17) is affine in CL"ab" To ensure sufficient stabilator authority to provide qmax the pitch-rate maneuverability requirement can be posed as the following LMI: (18) where + lstah C L"ab(nnminal) stabmax) Similar arguments can be used to obtain constraints on other angular rates. Constraint (18) …”

Section: Including Maneuverability Requirementsmentioning

confidence: 99%

“…Because of the availability of the component stability derivative data for the F-14 aircraft, a longitudinal control problem similar to the one discussed in Ref. 18 was selected for this example. Although the F-14 is not an RSS aircraft, the problem formulation can easily incorporate unstable aircraft dynamics.…”

Section: Example 1: Integrated Control Power-controller Design For F-mentioning

confidence: 99%

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Integrated aircraft-controller design using linear matrix inequalities

Niewoehner

Kaminer

1996

Journal of Guidance, Control, and Dynamics

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A new methodology is presented for solving the problem of optimizing the aircraft parameters, such as the size of its control surfaces, while meeting open-and closed-loop static and dynamic performance requirements. The approach proposed involves rewriting these requirements as linear matrix inequalities and solving a related constrained optimization problem for which efficient numerical solutions are available.

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Section: Niewoehner and Kaminermentioning

confidence: 73%

Section: Including Maneuverability Requirementsmentioning

confidence: 99%

Section: Including Maneuverability Requirementsmentioning

confidence: 99%

Section: Example 1: Integrated Control Power-controller Design For F-mentioning

confidence: 99%

See 2 more Smart Citations

Integrated aircraft-controller design using linear matrix inequalities

Niewoehner

Kaminer

1996

Journal of Guidance, Control, and Dynamics

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“…In order to deal with the uncertainties in the linear model, robust control techniques such as H 2 /H ∞ control theory and quantitative feedback theory are applied [3][4][5][6]. Niewoehner and Kaminer designed a carrier landing controller of the F-14 aircraft by translating typical Single-Input Single-Output (SISO) design specification into the H ∞ synthesis problem [3].…”

Section: Introductionmentioning

confidence: 99%

Constrained Adaptive Backstepping Controller Design for Aircraft Landing in Wind Disturbance and Actuator Stuck

Yoon¹,

Kim²,

Park³

2012

International Journal of Aeronautical and Space Sciences

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An adaptive backstepping controller is designed for the automatic landing of a fixed-wing aircraft. The backstepping control scheme is adopted by using the nonlinear six degree-of-freedom dynamics of the aircraft during the landing phase. The adaptive law is integrated along with the backstepping controller in order to estimate the aircraft modeling errors as well as the external disturbance. The dynamic constraints of the states and the actuator inputs are taken into account in the parameter adaptation. This is done to prevent an aggressive adaptation and to provide reliable control commands. Numerical simulations were performed to verify the performance of the proposed control law for the landing of the aircraft with the presence of gust and actuator stuck.

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