A review of mathematical modelling techniques for advanced rotorcraft configurations

Chen, Renliang; Yuan, Ye; Thomson, Douglas

doi:10.1016/j.paerosci.2020.100681

Cited by 20 publications

(8 citation statements)

References 125 publications

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“…A high-order nonlinear helicopter flight dynamics model was used for numerical simulation. The detailed flight dynamics modeling process can be obtained in references [23][24][25][26].…”

Section: Coupled Model Of Helicopter Flight Dynamics and Ship Airwake...mentioning

confidence: 99%

An Active Flow Control over the Ship Deck for Helicopter Shipboard Operations

Ye,

Chen,

2024

Aerospace

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This paper presents an active flow control of ship airwake over the deck to improve the safety of helicopter shipboard operations in various angles of wind over deck (WOD). Firstly, an integrated flight dynamics method coupled with ship airwake was developed to analyze the effect of ship airwake on the helicopter at various angles of WOD. Then, an active flow control strategy in various angles of WOD was investigated with the analysis of airwake distribution and the impact on helicopter trim flight. Finally, the effects of active blowing on airwake distribution, flight control inputs, control margins, and helicopter attitudes in trim were analyzed. The results indicate that the variation of the angles of WOD has a significant impact on flight controls and helicopter attitudes for helicopter hovering relative to ship motion. The nonuniformity of ship airwake can be effectively alleviated by applying active flow control. The variations of flight control inputs and helicopter attitude angles at trim states are reduced, which increases the control margins and contributes to enhancing the safety of helicopter shipboard operations.

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“…A high-order nonlinear helicopter flight dynamics model was used for numerical simulation. The detailed flight dynamics modeling process can be obtained in references [23][24][25][26].…”

Section: Coupled Model Of Helicopter Flight Dynamics and Ship Airwake...mentioning

confidence: 99%

An Active Flow Control over the Ship Deck for Helicopter Shipboard Operations

Ye,

Chen,

2024

Aerospace

Self Cite

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“…This is not a problem in this investigation as the manoeuvres of interest are not too aggressive. For the design of aggressive and acrobatic rotorcraft, it is better to use Quaternions (see [26,27] for more information).…”

Section: Kinematicsmentioning

confidence: 99%

Optimised Tuning of a PID-Based Flight Controller for a Medium-Scale Rotorcraft

Mpanza

Pedro

2021

Algorithms

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This paper presents the parameter optimisation of the flight control system of a singlerotor medium-scale rotorcraft. The six degrees-of-freedom (DOF) nonlinear mathematical model of the rotorcraft is developed. This model is then used to develop proportional–integral–derivative (PID)-based controllers. Since the majority of PID controllers installed in industry are poorly tuned, this paper presents a comparison of the optimised tuning of the flight controller parameters using particle swarm optimisation (PSO), genetic algorithm (GA), ant colony optimisation (ACO) and cuckoo search (CS) optimisation algorithms. The aim is to find the best PID parameters that minimise the specified objective function. Two trim conditions are investigated, i.e., hover and 10 m/s forward flight. The four algorithms performed better than manual tuning of the PID controllers. It was found, through numerical simulation, that the ACO algorithm converges the fastest and finds the best gains for the selected objective function in hover trim conditions. However, for 10 m/s forward flight trim, the GA algorithm was found to be the best. Both the tuned flight controllers managed to reject a gust wind of up to 5 m/s in the lateral axis in hover and in forward flight.

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“…However, the existence of a tip vortex makes the flow field of the rotor extremely complex [1,2]. In the field of helicopter aerodynamics and computational fluid dynamics (CFD), the accurate prediction for rotor flow field with vortex wake is still one of the most complex and challenging problems [3].…”

Section: Introductionmentioning

confidence: 99%

A Modified Fifth-Order WENO-HLLC Riemann Solver for Transonic Viscous Flows around Helicopter Rotor in Hover

Zhao

Cai

2022

Shock and Vibration

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This paper presents a modified fifth-order WENO-HLLC Riemann solver for the transonic compressible viscous flows around the helicopter rotor in hover. The HLLC approximate Riemann solver is proposed to discrete the convection term involving grid velocity of the Navier-Stokes equations. In order to solve the interface flow accurately, a modified fifth-order WENO scheme is presented by designing the smoothness indicators based on L 1 norm measurement. The improved WENO scheme can provide the optimal approximation order even at critical points. Numerical accuracy and robustness are validated by several benchmark inviscid flow problems. Then the numerical properties of the WENO-HLLC solver in conjunction with the implicit LU-SGS time integration method with high efficiency are further validated by simulating transonic viscous flows over RAE2822 airfoil and ONERA-M6 wing. The results show that the accuracy of calculating shock, discontinuity, and the vortex is significantly improved. Finally, the method is developed to compute the transonic vortex flow around the helicopter rotor with a domain discretized by overset grids. The results indicate that the proposed method is very robust and effective in acquiring high resolution for vortex wake.

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A review of mathematical modelling techniques for advanced rotorcraft configurations

Cited by 20 publications

References 125 publications

An Active Flow Control over the Ship Deck for Helicopter Shipboard Operations

An Active Flow Control over the Ship Deck for Helicopter Shipboard Operations

Optimised Tuning of a PID-Based Flight Controller for a Medium-Scale Rotorcraft

A Modified Fifth-Order WENO-HLLC Riemann Solver for Transonic Viscous Flows around Helicopter Rotor in Hover

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