Design and Flight Testing of Nonlinear Autoflight Control Laws Incorporating Direct Lift Control

Lombaerts, Thomas; Looye, Gertjan

doi:10.1007/978-3-642-38253-6_32

Cited by 6 publications

(3 citation statements)

References 7 publications

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“…Over the years, DLR has done flight experiments with various control laws based on classical NDI. 18,[20][21][22] These experiments were conducted using the now-retired VFW-16 ATTAS testbed.…”

Section: Introductionmentioning

confidence: 99%

Design and Flight Testing of Incremental Nonlinear Dynamic Inversion-based Control Laws for a Passenger Aircraft

Grondman

Looye

Kuchar

et al. 2018

2018 AIAA Guidance, Navigation, and Control Conference

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127

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This paper describes the design, implementation and flight testing of flight control laws based on Incremental Nonlinear Dynamic Inversion (INDI). The method compares commanded and measured accelerations to compute increments on the current control deflections. This results in highly robust control solutions with respect to model uncertainties as well as changes in aircraft dynamic characteristics of failure cases during flight. At the same time, the complexity of the algorithms is similar to classical ones. The key for practical implementation is in ensuring synchronization between angular acceleration and control deflection measurements or estimates. The underlying theory and practical design methods of INDI are very well understood, but implementation and testing has remained limited to sub-scale UAVs. The main contribution of this paper is to present the design and validation of manual attitude control functions for a Cessna Citation II experimental aircraft, covering control structure design, application of INDI, design optimization, robustness analyses, software implementation, ground and flight testing. For comparison, also control laws based on classical Nonlinear Dynamic Inversion were implemented and flown. The flight tests were highly successful and marked the first successful demonstration of INDI on a CS-25 certified aircraft. The flight test results proved that INDI clearly outperforms NDI and provided valuable lessons-learnt for future applications. Nomenclature A x , A y , A z Specific forces along body X/Y/Z axis, g C Dimensionless coefficient F Force, N J Inertia matrix, kg•m 2 J Moment of Inertia, kg•m 2 K Gain M Moment, Nm M Mach number N 1 Fan speed, s −1 S Wing surface area, m 2 V Velocity vector, m/s V Airspeed, m/s a x , a y , a z Linear accelerations along body X/Y/Z axis, m/s 2 b Wing span, m 2 c Mean aerodynamic chord, m

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Section: Introductionmentioning

confidence: 99%

Design and Flight Testing of Incremental Nonlinear Dynamic Inversion-based Control Laws for a Passenger Aircraft

Grondman

Looye

Kuchar

et al. 2018

2018 AIAA Guidance, Navigation, and Control Conference

Self Cite

127

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“…In addition, for research on aircraft motion, the literature [ 30 ] proposed a new test platform system for different vertical take-off and landing multirotor UAVs that can achieve unrestricted aircraft motion along all axes. The literature [ 31 ] introduces direct lift control (DLC) into the flight control system. Simulations and flight tests show that accurate flight path tracking can be achieved by introducing DLC.…”

Section: Introductionmentioning

confidence: 99%

Elman Neural Network‐Based Direct Lift Automatic Carrier Landing Nonsingular Terminal Sliding Mode Fault‐Tolerant Control System Design

Zhu

Han

2023

Computational Intelligence and Neuroscience

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The purpose of this paper is to develop the control system using the Elman neural network (ENN) and nonsingular terminal sliding mode control (NTSMC) to improve the automatic landing capability of carrier-based aircraft based on direct lift control (DLC) when subjected to carrier air-wake disturbance and actuator failure. First, the carrier-based aircraft landing model is derived. Then, the NTSMC is proposed to ensure the system’s robustness and achieve accurate trajectory tracking performance in a finite time. Due to the inclusion of nonsingularity in NTSMC, the steady-state response of the control system can be effectively improved. In addition, the ENN is derived using an adaptive learning algorithm to approximate the actuator faults and system uncertainties. To further ensure the accurate tracking of the ideal glide path by the carrier-based aircraft, the NTSMC system using an ENN estimator is proposed. Finally, this method is tested by adding different types of actuator failures. The simulation results show that the designed longitudinal fault-tolerant carrier landing system has strong robustness and fault-tolerant ability and improves the accuracy of carrier-based aircraft landing trajectory tracking.

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“…In the 21st century, nonlinear control methods have been gradually applied to the DLC design system [13] . Thomas Lombaerts and Gertjan Looye [14] integrated DLC into a nonlinear automatic flight control system. The flight tests were conducted on ATTAS, and a simulation of VFW 614 was performed.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Comprehensive Decoupling Controller Based on Direct Lift Control for Carrier Landing

Wen-hai

Liting²,

Zhang³

et al. 2022

IEEE Access

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In this study, the direct lift control (DLC) method was introduced into the carrier landing control law. Characterized by quick response and high accuracy, the DCL method can help us overcome the "backhoe" character, reduce the pilot's control burden, and improve the accuracy and safety of carrier landing. A two-level integrated landing controller was designed by combining the prescribed performance nonlinear dynamic inversion and control allocation algorithm. The decoupling between longitudinal trajectory and attitude controls, as well as the decoupling between horizontal control and longitudinal motion, was considered. First, a six-degree-of-freedom nonlinear model of an aircraft was established. Second, a dynamic inverse loop was organically connected with the control allocation loop by setting the intermediate virtual control vector. And the control performance of the dynamic inverse control loop was improved by prescribing the error vector constraint equation. Finally, the simulation results showed that the designed direct lift controller can correct the vertical path while keeping the angle of attack and flight speed stable and prevent the aircraft from losing altitude when aligning with the center line. Overall, the designed direct lift control system can improve trajectory control efficiency in carrier landing and reduce pilots' burden.

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Design and Flight Testing of Nonlinear Autoflight Control Laws Incorporating Direct Lift Control

Cited by 6 publications

References 7 publications

Design and Flight Testing of Incremental Nonlinear Dynamic Inversion-based Control Laws for a Passenger Aircraft

Design and Flight Testing of Incremental Nonlinear Dynamic Inversion-based Control Laws for a Passenger Aircraft

Elman Neural Network‐Based Direct Lift Automatic Carrier Landing Nonsingular Terminal Sliding Mode Fault‐Tolerant Control System Design

Nonlinear Comprehensive Decoupling Controller Based on Direct Lift Control for Carrier Landing

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