TY - GEN
T1 - Estimation of wind field velocity and aircraft states with an F-16 lateral guidance control system
AU - Akmal, Hassan
AU - Qu, Yaohong
N1 - Publisher Copyright:
© 2015 IEEE.
PY - 2015/9/28
Y1 - 2015/9/28
N2 - Bearing in mind the risks aviation industry is facing recently, this paper proposes a wind field estimation formulation for an F-16 fighter aircraft. Focus of the work is two-fold. A lateral-directional, non-linear guidance controller is developed first to ensure tight ground track control without violating saturation limits of bank angles. For trajectory tracking, path following vectorial computations are performed for both straight and curved tracks in North-East-Down (NED) as well as in Earth-Centred-Earth-Fixed (ECEF) reference coordinate systems. Furthermore, for the wind field estimation based on generated flight data and a Frozen Dryden Wind Turbulence Model, a Discrete-Time Kalman Filter (DKF) is employed. Simulations are run for real flight scenarios with noisy sensors and gust winds. The simulation analysis highlights the effectiveness of the proposed technique in comparison to the conventional direct method estimation used for unmanned aerial vehicles (UAVs). It is also shown that the suggested method is capable of providing smoothed estimates for the aircraft attitude states and sideslip angle.
AB - Bearing in mind the risks aviation industry is facing recently, this paper proposes a wind field estimation formulation for an F-16 fighter aircraft. Focus of the work is two-fold. A lateral-directional, non-linear guidance controller is developed first to ensure tight ground track control without violating saturation limits of bank angles. For trajectory tracking, path following vectorial computations are performed for both straight and curved tracks in North-East-Down (NED) as well as in Earth-Centred-Earth-Fixed (ECEF) reference coordinate systems. Furthermore, for the wind field estimation based on generated flight data and a Frozen Dryden Wind Turbulence Model, a Discrete-Time Kalman Filter (DKF) is employed. Simulations are run for real flight scenarios with noisy sensors and gust winds. The simulation analysis highlights the effectiveness of the proposed technique in comparison to the conventional direct method estimation used for unmanned aerial vehicles (UAVs). It is also shown that the suggested method is capable of providing smoothed estimates for the aircraft attitude states and sideslip angle.
KW - Discrete-Time Kalman Filter
KW - Lateral Guidance and Control
KW - Trajectory Tracking
KW - UAVs
KW - Wind Field Estimation
KW - Wind Modelling
UR - http://www.scopus.com/inward/record.url?scp=84959932365&partnerID=8YFLogxK
U2 - 10.1109/ICInfA.2015.7279668
DO - 10.1109/ICInfA.2015.7279668
M3 - 会议稿件
AN - SCOPUS:84959932365
T3 - 2015 IEEE International Conference on Information and Automation, ICIA 2015 - In conjunction with 2015 IEEE International Conference on Automation and Logistics
SP - 2293
EP - 2298
BT - 2015 IEEE International Conference on Information and Automation, ICIA 2015 - In conjunction with 2015 IEEE International Conference on Automation and Logistics
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2015 IEEE International Conference on Information and Automation, ICIA 2015 - In conjunction with 2015 IEEE International Conference on Automation and Logistics
Y2 - 8 August 2015 through 10 August 2015
ER -