The use of modern robust control design methods in the autoland system design process - the REAL project

Rouwhorst, W.F.J.A.

doi:10.1016/s1290-0958(01)90090-5

Cited by 3 publications

(1 citation statement)

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“…The optimisation problem described by eq. (23) to (26) is formulated automatically by the MOPS environment. Adding optimisation sub-tasks or model cases, and setting properties of criteria can be done with the help of a graphical user interface, or alternatively via scripts.…”

Section: Parameter Optimization and Linear Stability Analysismentioning

confidence: 99%

Design and flight testing of manual nonlinear flight control laws

Lombaerts

Looye

2011

AIAA Guidance, Navigation, and Control Conference

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This paper describes the design of a manual flight controller, based upon nonlinear model-based control laws. These control laws include the previously developed concept of Pseudo Control Hedging (PCH). This PCH algorithm adapts the reference model for the system output in case of unachievable commands due to control input saturation. This control algorithm has been applied in the body angular rate control loops of a high fidelity simulation model of the VFW-614 ATTAS (Advanced Technologies Testing Aircraft System) laboratory aircraft, where its beneficial influence has been illustrated. Test flights have been performed with ATTAS to evaluate the flight control technique in a relevant environment. Nomenclaturegain L; M ; N combined aerodynamic and thrust moment around the body X/Y/Z axis [Nm] N 1 fan speed [s -1 ] OS overshoot [rad] S wing area [m 2 ] V airspeed [m/s] b wingspan [m] c mean aerodynamic chord [m] g gravity constant [m/s 2 ] n x ; n y ; n z load factor along body X/Y/Z axis [-] p; q; r roll, pitch and yaw rate around the body X/Y/Z axis [rad/s] u input u b ; v b ; w b airspeed velocity components along body X/Y/Z axis [m/s] u e ; v e ; w e airspeed velocity components along earth fixed X/Y/Z axis [m/s] x; y; z position coordinates along X/Y/Z axis [m] (reference frame varies) x state vector Subscript 0 constant term A with respect to aerodynamic reference frame bwith respect to body fixed reference frame e with respect to earth fixed reference frame k with respect to kinematic reference frame a; e; r aileron, elevator and rudder c; comm commanded * Researcher,

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Section: Parameter Optimization and Linear Stability Analysismentioning

confidence: 99%