Rotor Dynamic Wake Distortion Model for Helicopter Maneuvering Flight

Zhao, Jiupeng

doi:10.4050/jahs.49.414

Cited by 27 publications

(39 citation statements)

References 38 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This observation is in agreement with typical trends reported by other investigators (Ref. 26). A small improvement in the on-axis response can also be observed in Fig.…”

Section: Nonlinear Response To Pilot Control Inputssupporting

confidence: 94%

“…12,13), a dynamic wake distortion model (Ref. 26), and an unsteady nonlinear blade element aerodynamics model (Ref. 27).…”

Section: -3mentioning

confidence: 99%

“…27), and the Zhao-Prasad dynamic wake distortion model (Ref. 26). Experimentally derived quasi-steady airfoil data are incorporated for the calibration of the Leishman-Beddoes model.…”

Section: Integrated Aeroelastic Rotor-aircraft Modelmentioning

confidence: 99%

See 2 more Smart Citations

Helicopter Rotor Blade Flexibility Simulation for Aeroelasticity and Flight Dynamics Applications

Goulos¹,

Pachidis²,

Pilidis³

2014

j am helicopter soc

View full text Add to dashboard Cite

This paper presents a mathematical model for the simulation of rotor blade flexibility in real-time helicopter flight dynamics applications that also employs sufficient modeling fidelity for prediction of structural blade loads. A matrix/vector-based formulation is developed for the treatment of elastic blade kinematics in the time domain. A novel, second-order-accurate, finite-difference scheme is employed for the approximation of the blade motion derivatives. The proposed method is coupled with a finite-state induced-flow model, a dynamic wake distortion model, and an unsteady blade element aerodynamics model. The integrated approach is deployed to investigate trim controls, stability and control derivatives, nonlinear control response characteristics, and structural blade loads for a hingeless rotor helicopter. It is shown that the developed methodology exhibits modeling accuracy comparable to that of non-real-time comprehensive rotorcraft codes. The proposed method is suitable for real-time flight simulation, with sufficient fidelity for simultaneous prediction of oscillatory blade loads.Nomenclature A flap/lag/torsion Lagrange

show abstract

“…This observation is in agreement with typical trends reported by other investigators (Ref. 26). A small improvement in the on-axis response can also be observed in Fig.…”

Section: Nonlinear Response To Pilot Control Inputssupporting

confidence: 94%

“…12,13), a dynamic wake distortion model (Ref. 26), and an unsteady nonlinear blade element aerodynamics model (Ref. 27).…”

Section: -3mentioning

confidence: 99%

See 1 more Smart Citation

Helicopter Rotor Blade Flexibility Simulation for Aeroelasticity and Flight Dynamics Applications

Goulos¹,

Pachidis²,

Pilidis³

2014

j am helicopter soc

View full text Add to dashboard Cite

show abstract

“…This is due to the fact that the dominant physical phenomena associated with rotor dynamics [4], inflow dynamics [27], unsteady nonlinear aerodynamics [29], and dynamic wake distortion [30] are all included in the analysis. It can thus be con cluded that the proposed rotor model can be deployed for the extraction of equivalent dynamic response time-delays from first principles, without any empiricism involved.…”

Section: Transient Rotor Response To Control Inputsmentioning

confidence: 99%

“…The developed mathematical approach is coupled numerically with the Peters-He finite-state induced flow model [27,28], the LeishmanBeddoes unsteady nonlinear blade element aerodynamics model [29], and the Zhao-Prasad dynamic wake distortion model [30], The rotor blade's natural vibration characteristics obtained from the Lagrangian formulation are utilized. The dynamic response of the elastic blades to external aerodynamic and inertial forcing is calculated using a fifth order accurate numerical evaluation scheme of the convolution integral.…”

Section: Integrated Aero-elastic Rotor-fuselage Modelmentioning

confidence: 99%

Real-Time Aero-elasticity Simulation of Open Rotors With Slender Blades for the Multidisciplinary Design of Rotorcraft

Goulos

Pachidis

2014

Journal of Engineering for Gas Turbines and Power

View full text Add to dashboard Cite

This paper elaborates on the theoretical development of a mathematical approach, tar geting the real-time simulation of aero-elasticity for open rotors with slender blades, as employed in the majority of rotorcraft. A Lagrangian approach is formulated for the rapid estimation of natural vibration characteristics of rotor blades with nonuniform structural properties. Modal characteristics obtained from classical vibration analysis methods are utilized as assumed deformation functions. Closed form integral expressions are incorporated, describing the generalized centrifugal forces and moments acting on the blade. The treatment of three-dimensional elastic blade kinematics in the timedomain is thoroughly discussed. In order to ensure robustness and establish applicability in real time, a novel, second-order accurate, finite-difference scheme is utilized for the temporal discretization of elastic blade motion. The developed mathematical approach is coupled with a finite-state induced flow model, an unsteady blade element aerodynamics model, and a dynamic wake distortion model. The combined formulation is implemented in an existing helicopter flight mechanics code. The aero-elastic behavior of a full-scale hingeless helicopter rotor has been investigated. Results are presented in terms of rotor blade resonant frequencies, rotor trim performance, oscillatory structural blade loads, and transient rotor response to control inputs. Extensive comparisons are carried out with wind tunnel (WT) and flight test (FT) measurements found in the open literature as well as with nonreal-time comprehensive analysis methods. It is shown that the proposed approach exhibits good agreement with measured data regarding trim performance and transient rotor response characteristics. Accurate estimation of structural blade loads is demonstrated, in terms of both amplitude and phase, up to the third harmonic component o f oscillatory loading.It is shown that the developed model can be utilized for real-time simulation on a modern personal computer. The proposed methodology essentially con stitutes an enabling technology for the multidisciplinary design of rotorcraft, when a compromise between simulation fidelity and computational efficiency has to be sought for in the process of model development.

show abstract

Numerical prediction and experimental validation of an onboard rotor under bending

et al. 2021

View full text Add to dashboard Cite

Rotor Dynamic Wake Distortion Model for Helicopter Maneuvering Flight

Abstract: Combined effect of main rotor wake distortion and main rotor/tail rotor/empennage interaction on the on-axis roll rate response of a UH-60 Black Hawk helicopter at 40 knots flight speed to the lateral cyclic control stick doublet input of Figure 3.

Cited by 27 publications

References 38 publications

Helicopter Rotor Blade Flexibility Simulation for Aeroelasticity and Flight Dynamics Applications

Helicopter Rotor Blade Flexibility Simulation for Aeroelasticity and Flight Dynamics Applications

Real-Time Aero-elasticity Simulation of Open Rotors With Slender Blades for the Multidisciplinary Design of Rotorcraft

Numerical prediction and experimental validation of an onboard rotor under bending

Contact Info

Product

Resources

About