Study on Control Strategy for Tilt-rotor Aircraft Conversion Procedure

Yan, Xufei; Chen, Renliang; Lou, Bin; Xie, Ye; Xie, Anhuan; Zhang, Dan

doi:10.1088/1742-6596/1924/1/012010

Cited by 7 publications

(10 citation statements)

References 7 publications

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“…where η s is the propeller slipstream correction factor, B is the propeller tilt Angle, c is the average chord length of the wing, μ max is the maximum advance ratio of the propeller wake deviated from the wing, a and b are 1.386 and 3.114 respectively [6] . In this paper, the aerodynamic coefficient is calculated by CFD.…”

Section: Matma-2023mentioning

confidence: 99%

Research on transition corridor of distributed tilting power configuration

Chen,

Yang,

Zhang

et al. 2024

J. Phys.: Conf. Ser.

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For a distributed tilt-power configuration aircraft, the transition corridor was studied based on limited conditions such as wing lift characteristics and propeller power requirement. By establishing the dynamic model of each component and balancing according to the balance equation, the boundary of the transition corridor of distributed tilting dynamic configuration is determined. The results show that the minimum forward flight speed required for a low Angle of attack is less than that for a high Angle of attack; the wing lift characteristic high-speed boundary and the propeller power limit boundary together form the high-speed boundary of the transition corridor.

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Section: Matma-2023mentioning

confidence: 99%

Research on transition corridor of distributed tilting power configuration

Chen,

Yang,

Zhang

et al. 2024

J. Phys.: Conf. Ser.

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show abstract

“…The control process during conversion is complicated because of the cooperation between the lift and thrust, complex unsteady aerodynamic effects, body motion, and inertial coupling, as well as the control transition between helicopter mode and fixed-wing mode [2][3][4]. In the conversion procedure, the pilot not only has to focus on cockpit control but also pay attention to the tilting of the nacelles, which significantly increases the pilot workload [5,6].…”

Section: Introductionmentioning

confidence: 99%

Research on Pilot Control Strategy and Workload for Tilt-Rotor Aircraft Conversion Procedure

Yan¹,

Yuan²,

Chen³

2023

Preprint

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This paper studies the pilot control strategy and workload of tilt-rotor aircraft dynamic conversion procedure between helicopter mode and fixed-wing mode. A nonlinear flight dynamics model of tilt-rotor aircraft with full flight modes is established. On this basis, a nonlinear optimal control model of dynamic conversion is constructed, considering factors such as conversion corridor limitations, pilot control, flight attitude, engine rated power, and wing stall effects. To assess pilot workload, an analytical method based on wavelet transform is proposed, which examines the mapping relationship between pilot control input's amplitude, constituent frequencies, and control tasks. By integrating the nonlinear optimal control model and the pilot workload evaluation method, the analysis of pilot control strategy and workload during the conversion procedure is conducted, leading to the identification of strategies to reduce pilot workload. The results indicate that incorporating the item of pilot workload in the performance index results in a notable reduction in the magnitude of collective stick inputs and longitudinal stick inputs. Moreover, it facilitates smoother adjustments in altitude and pitch attitude. Additionally, the conversion of the engine nacelle can be achieved at a lower and constant angular velocity. In summary, the conversion and reconversion procedures are estimated to have a low workload (Level 1 ~ Level 2), with relatively simple and easy manipulation for the pilot.

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Section: Introductionmentioning

confidence: 99%

Research on Pilot Control Strategy and Workload for Tilt-Rotor Aircraft Conversion Procedure

Yan,

Yuan,

Chen

2023

Aerospace

Self Cite

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This paper studies the pilot control strategy and workload of a tilt-rotor aircraft dynamic conversion procedure between helicopter mode and fixed-wing mode. A nonlinear flight dynamics model of tilt-rotor aircraft with full flight modes is established. On this basis, a nonlinear optimal control model of dynamic conversion is constructed, considering factors such as conversion corridor limitations, pilot control, flight attitude, engine rated power, and wing stall effects. To assess pilot workload, an analytical method based on wavelet transform is proposed, which examines the mapping relationship between pilot control input amplitude, constituent frequencies, and control tasks. By integrating the nonlinear optimal control model and the pilot workload evaluation method, an analysis of the pilot control strategy and workload during the conversion procedure is conducted, leading to the identification of strategies to reduce pilot workload. The results indicate that incorporating the item of pilot workload in the performance index results in a notable reduction in the magnitude of collective stick inputs and longitudinal stick inputs. Moreover, it facilitates smoother adjustments in altitude and pitch attitude. Additionally, the conversion of the engine nacelle can be achieved at a lower and constant angular velocity. In summary, the conversion and reconversion procedures are estimated to have a low workload (level 1~2), with relatively simple and easy manipulation for the pilot.

show abstract

Study on Control Strategy for Tilt-rotor Aircraft Conversion Procedure

Cited by 7 publications

References 7 publications

Research on transition corridor of distributed tilting power configuration

Research on transition corridor of distributed tilting power configuration

Research on Pilot Control Strategy and Workload for Tilt-Rotor Aircraft Conversion Procedure

Research on Pilot Control Strategy and Workload for Tilt-Rotor Aircraft Conversion Procedure

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