### Abstract

Original language | English |
---|---|

Publication status | Submitted - 25 Jan 2019 |

### Fingerprint

### Cite this

**Neural-Network Bilinear Gain-Scheduling Control for B747-100 Longitudinal Dynamics.** / Elarbi, Ezzeddin M.; Laila, Dina Shona; Horri, Nadjim.

Research output: Contribution to conference › Paper

}

TY - CONF

T1 - Neural-Network Bilinear Gain-Scheduling Control for B747-100 Longitudinal Dynamics

AU - Elarbi, Ezzeddin M.

AU - Laila, Dina Shona

AU - Horri, Nadjim

PY - 2019/1/25

Y1 - 2019/1/25

N2 - A Gaussian radial basis function neural network was applied to control the longitudinal dynamics of Boeing 747-100. Bilinear interpolation calibrates the responses to allow for gain scheduled control within the whole flight envelope. The baseline responses are produced from the simulations based on Linear Quadratic Regulator (LQR) control combining elevator and throttle commands at three trim conditions on Mach number (M) and altitudes: (M=0.2,0m), (M=0.5, 6096m) and (M=0.9, 12192m). The Latin hypercube is employed to uniformly discretize the flight envelope with Mach numbers ranging from 0.2 to 0.9 and altitudes from 0 to 12192m. The steady state response surfaces of longitudinal references are achieved based on gains smoothly satisfying closed loop flying qualities. The elevator and throttle inputs can be adjusted to maintain the center of gravity within admissible limits over the entire flight envelope. The pitch trim condition can be autotuned by autothrottle for a given center of gravity location.

AB - A Gaussian radial basis function neural network was applied to control the longitudinal dynamics of Boeing 747-100. Bilinear interpolation calibrates the responses to allow for gain scheduled control within the whole flight envelope. The baseline responses are produced from the simulations based on Linear Quadratic Regulator (LQR) control combining elevator and throttle commands at three trim conditions on Mach number (M) and altitudes: (M=0.2,0m), (M=0.5, 6096m) and (M=0.9, 12192m). The Latin hypercube is employed to uniformly discretize the flight envelope with Mach numbers ranging from 0.2 to 0.9 and altitudes from 0 to 12192m. The steady state response surfaces of longitudinal references are achieved based on gains smoothly satisfying closed loop flying qualities. The elevator and throttle inputs can be adjusted to maintain the center of gravity within admissible limits over the entire flight envelope. The pitch trim condition can be autotuned by autothrottle for a given center of gravity location.

M3 - Paper

ER -