Using Control Redundancy for Power and Vibration Reduction on a Compound Helicopter at High Speeds

Jacobellis, George; Gandhi, Farhan; Floros, Matthew

doi:10.4050/jahs.63.032009

Cited by 11 publications

(5 citation statements)

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“…The variable speed transmission system studied in this study is applicable to aviation transmission, which can achieve different propeller tip speed in high speed cruise state and hovering state of helicopters [ 1 ]. Compared with the constant rotor speed scheme, by changing the main rotor speed to react to a variety of flight circumstances, it is effective in solving rotor noise, breaking forward flight speed, increasing payload and range, reducing fuel consumption and maintenance costs, etc [ 2 ].…”

Section: Introductionmentioning

confidence: 99%

Study on nonlinear dynamics characteristics of dual speed dual clutch transmission system based on bond graph

Wu,

Yan,

Liu

et al. 2023

Heliyon

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Section: Introductionmentioning

confidence: 99%

Study on nonlinear dynamics characteristics of dual speed dual clutch transmission system based on bond graph

Wu,

Yan,

Liu

et al. 2023

Heliyon

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“…Kimura et al [4] studied the change in forward flight performance when increasing the swept-back angle of the paddle of a high-speed helicopter based on CFD techniques. Reddinger et al [5] achieved the minimization of power and propeller vibration by studying the redundancy control of a compound helicopter. Farassat et al [6] proposed an acoustic analogy formulation to predict rotor impulse noise in high-speed helicopters.…”

Section: Introductionmentioning

confidence: 99%

Analysis of Aerodynamic Characteristics of Different Tail Configurations of Compound High-speed Helicopters

Yu,

Li,

Baoyin

2023

J. Phys.: Conf. Ser.

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When a compound high-speed helicopter is in forward flight, there are serious aerodynamic disturbances among the fuselage components, among which the tail configuration has a greater influence on its aerodynamic performance. To study the influence of different tail configurations on aerodynamic performance, the flow field of a compound high-speed helicopter in forward flight was numerically simulated based on the commercial software XFlow. Firstly, the ROBIN standard helicopter fuselage model was calculated to verify the scientific validity of the method. Then, the aerodynamic data of a high-speed helicopter was analyzed for different tail configurations in forward flight with different angles of attack and yaw. The results show that the V-tail configuration has the lowest lift and resistance coefficients and the best longitudinal manoeuvrability and stall characteristics; the conventional tail configuration has the highest lift-to-resistance ratio and the fastest wake decay; the lateral stability of the V-tail and conventional tail configurations is weaker than that of the H-tail and fixed tail configurations; and the presence of the vertical tail in the tail increases the pressure value around the wing surface.

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“…Currently, the forward flight speeds of conventional civilian and military helicopters are limited to approximately 300-350 km/h, which does not satisfy the design goals and mission requirements of high-speed compound helicopters [1]. With innovation and breakthroughs in power plants and configurations, the horizontal flight speed of fifthgeneration helicopters has exceeded 400 km/h [2].…”

Section: Introductionmentioning

confidence: 99%

Design and Optimization of Low Impact Shift Control Strategy for Aviation Transmission Power System Based on Response Surface Methodology

Wu,

Yan,

Zheng

et al. 2023

Applied Sciences

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The utilization of a variable-speed power system significantly improves the forward flight speed and cruising range of the helicopter. Nevertheless, the shock of speed and torque during the shift process brings stability and safety problems that cannot be ignored. Thus, swift and stable shift control is a key issue in the research on aviation power systems. This study focuses on the design and optimization of low-impact shift control strategies for a variable-speed power system, which involves multiple control variables, long adjustment times, and uncontrollable risks due to the nonsteady state. A comprehensive power system model that integrates the engine, a two-speed dual-clutch transmission system, and the main rotor was proposed. By selecting the engine fuel flow, friction clutch hydraulic pressure, and rotor pitch angle as input signals, regression fitting models between the input signals’ starting time points and speed or torque shock were obtained using Response Surface Methodology (RMS). The interaction effect of multiple time series was analyzed, and four kinds of low-impact nonlinear programming multi-objective optimized models for speed or torque are proposed. The results indicate that the P values of the RMS fitting models at upshift and downshift are less than 0.0001 and 0.05, respectively, which are highly significant and can effectively predict the shift dynamic response; under the optimized upshift and downshift control strategy, the speed and torque shock are reduced by 5–10%.

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Using Control Redundancy for Power and Vibration Reduction on a Compound Helicopter at High Speeds

Cited by 11 publications

References 0 publications

Study on nonlinear dynamics characteristics of dual speed dual clutch transmission system based on bond graph

Study on nonlinear dynamics characteristics of dual speed dual clutch transmission system based on bond graph

Analysis of Aerodynamic Characteristics of Different Tail Configurations of Compound High-speed Helicopters

Design and Optimization of Low Impact Shift Control Strategy for Aviation Transmission Power System Based on Response Surface Methodology

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