Powered Yaw Control for Distributed Electric Propulsion Aircraft: A Model Predictive Control Approach

Kou, Peng; Wang, Jing; Liang, Deliang

doi:10.1109/tte.2021.3068724

Cited by 23 publications

(5 citation statements)

References 17 publications

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“…It can be seen that the thrust mapping, logically, favours the outermost propulsors for creating yawing moment. (Similar to Kou et al [27], where also the outboard controllers are prioritised by the yaw command though with a much more sophisticated control scheme). This is because the outermost propulsors have the largest moment arm; therefore, reducing their thrust results in the highest available thrust, whilst simultaneously satisfying a specific yaw command.…”

Section: Directional Control Under Inoperative Conditionsmentioning

confidence: 99%

“…This has been used to create reference charts with delta factors that can easily be applied in design. A recent article by Kou et al [27] includes aero-propulsive effects through the VSPAERO toolkit provided through OpenVSP in the development of a model predictive control scheme for powered yaw control. Nguyen Van et al [24,25] conclude that differential thrust can maintain the control of the aircraft at low airspeed due to high control effectiveness and that oversized vertical tailplanes reduce the ability to achieve sideslip angles at high velocities.…”

Section: Introductionmentioning

confidence: 99%

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Flight dynamics and control assessment for differential thrust aircraft in engine inoperative conditions including aero-propulsive effects

Hoogreef

Soikkeli²

2022

CEAS Aeronaut J

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Differential thrust can be used for directional control on distributed electric propulsion aircraft. This paper presents an assessment of flight dynamics and control under engine inoperative conditions at minimum control speed for a typical distributed propulsion aircraft employing differential thrust. A methodology consisting of an aerodynamic data acquisition module and a non-linear six-degrees-of-freedom flight dynamics model is proposed. Directional control is achieved using a controller to generate a yaw command, which is distributed to the propulsors through a thrust mapping approach. A modified version of the NASA X-57 aircraft is selected for case studies, where the engine inoperative condition is considered to impact the three leftmost propulsors during climb at minimum control speed. The objective also includes the assessment of the impact of the aero-propulsive coupling for such an aircraft during a failure case. Results show that during the recovery manoeuvre, the aircraft experiences a 78% reduction in total thrust and 30% reduction in total lift caused by the aggressive yaw control effort required to control the heading of the aircraft. Consequently, the powered-stall speed is increased, and the aircraft temporarily loses altitude during the recovery manoeuvre. Differential thrust provides sufficient yaw authority during the engine inoperative condition, and is, therefore, seen to potentially replace the functionality of the rudder for the climb condition that was studied. Additionally, reduction of the vertical tail area was explored and seen to be possible if the response time of the system is low enough. For the studied configuration, this required a response within 400 ms for reduced vertical tail areas.

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Section: Directional Control Under Inoperative Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Flight dynamics and control assessment for differential thrust aircraft in engine inoperative conditions including aero-propulsive effects

Hoogreef

Soikkeli²

2022

CEAS Aeronaut J

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“…Unlike conventional turboprops, electric aircraft use electric motors with the propellers to power the aircraft [5,6]. HC-IPMSM electric propulsion system is shown in Figure 1.…”

Section: Introductionmentioning

confidence: 99%

Analytical model of no‐load axial force for electric propulsion conical motor in electric aircraft

Fan,

Liang,

Liang

et al. 2023

IET Electric Power Appl

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In the field of electric aircraft, the axial force of the conical motor is used to offset propeller thrust and reduce bearing wear. For the problem of accurate calculation of the no‐load axial force of the conical motor, combined with the characteristics that the rotor magnetic bridge of the hybrid conical inner‐mounted permanent magnet synchronous motor (HC‐IPMSM) is easy to be saturated and difficult to be calculated analytically, an equivalent analytical calculation method is proposed. According to the principle of constant air‐gap magnetic flux, the HC‐IPMSM is equivalent to many cylindrical surface‐mounted permanent magnet synchronous motors (CY‐SPMSM), and an analytical model is gained. Combining with the scalar magnetic potential Laplace equation and Poisson equation, the air‐gap flux density distribution on the rotor surface is calculated. And finally, the no‐load axial force of the motor is obtained by using the cone angle and the Maxwell stress method. Simulation and experiments verify the correctness and validity of the analytical model.

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“…However, the traditional nominal control does not consider the rudder failure systems [7][8][9]. Due to the exposure of the VSF rudder surface to air ow, it is easy to have partial or complete fault of the rudder surface [10,11] in a high altitude and high-speed ight environment, especially in the case of multiple rudder faults when the VSF is making a large maneuver. It seriously a ects the handling performance of the aircraft and even endangers the safety of the system [12].…”

Section: Introductionmentioning

confidence: 99%

Improved Adaptive Fault-Tolerant Control of a Variable Structure Fighter with Multiple Faults Based on an Extended Observer

Sun

Yang

2022

Mathematical Problems in Engineering

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In this paper, an improved adaptive fault-tolerant control (FTC) scheme is presented based on an extended state observer (ESO) for a highly maneuverable variable structure fighter (VSF) with simultaneous faults of the rudder surface and sensor. The feedback linearization model of the attitude system with faults and external disturbances is introduced. In order to realize the real-time observation of the rudder and sensor faults, a neural network estimator is used to approximate sensor faults, and the ESO is designed to estimate the rudder surface fault and attitude variables. On this basis, the estimated value is used to replace the measured value for state variables to design the adaptive fault-tolerant controller for the inner and outer loop, combined with the second-order command filter to offset the phenomenon of backstepping differential amplification system noise. Finally, the proposed FTC scheme realizes the variable structure self-repairing of multiple positions, multiple types of faults in VSF using fault estimation. The Lyapunov theory and Barbalat’s lemma prove the stability of the designed observer and controller. The effectiveness of the FTC scheme is verified by a simulation experiment.

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Powered Yaw Control for Distributed Electric Propulsion Aircraft: A Model Predictive Control Approach

Cited by 23 publications

References 17 publications

Flight dynamics and control assessment for differential thrust aircraft in engine inoperative conditions including aero-propulsive effects

Flight dynamics and control assessment for differential thrust aircraft in engine inoperative conditions including aero-propulsive effects

Analytical model of no‐load axial force for electric propulsion conical motor in electric aircraft

Improved Adaptive Fault-Tolerant Control of a Variable Structure Fighter with Multiple Faults Based on an Extended Observer

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