A5005175747- Computational Fluid Dynamics and Aerodynamics
- Fluid Dynamics and Turbulent Flows
- Aerodynamics and Acoustics in Jet Flows
- Aerodynamics and Fluid Dynamics Research
- Plasma and Flow Control in Aerodynamics
- Acoustic Wave Phenomena Research
- Aeroelasticity and Vibration Control
- Turbomachinery Performance and Optimization
- Icing and De-icing Technologies
- Aerospace and Aviation Technology
- Advanced Aircraft Design and Technologies
- Vehicle Noise and Vibration Control
- Aerospace Engineering and Control Systems
- Biomimetic flight and propulsion mechanisms
- Fluid Dynamics and Vibration Analysis
- Aerospace Engineering and Energy Systems
- Cryospheric studies and observations
- Wind and Air Flow Studies
- Adaptive Dynamic Programming Control
- Smart Materials for Construction
- Adaptive Control of Nonlinear Systems
- Gas Dynamics and Kinetic Theory
- Probabilistic and Robust Engineering Design
- Electromagnetic Scattering and Analysis
- Topology Optimization in Engineering
Nanjing University of Aeronautics and Astronautics
2015-2024
University of Glasgow
2019
Xuzhou Construction Machinery Group (China)
2005
An event-triggered-based (ETB) discrete-time neural control is studied for a quadrotor unmanned aerial vehicle (UAV) with external disturbances and input saturation by using the disturbance observer (DTDO). First, ETB mechanism of network given Sigmoid-type function employed to tackle problem saturation. Then, DTDO designed utilized ensure boundedness virtual signal. Combining tracking differentiator backstepping technology, stability closed-loop system analyzed. Finally, experiment results...
A robust unsteady rotor flowfield solver CLORNS code is established to predict the complex aerodynamic characteristics of flowfield. In order handle difficult problem about grid generation around with shape in this CFD code, a parameterized generated method established, and moving-embedded grids are constructed by several proposed universal methods. work, Reynolds-Averaged Navier-Stokes (RANS) equations Spalart-Allmaras selected as governing helicopter rotor. The discretization convective...
Traditional numerical simulation methods for airfoil flowfields are complex and time-consuming, deep learning-based inference Reynolds-averaged Navier–Stokes equations (RANS) solutions of transonic airfoils have limitations in terms their robustness generalization. A novel data-driven method named as attention UNet (AU)-RANS is proposed efficient accurate prediction around with strong compressibility large-scale turbulent separation. First, to enhance the learning boundary flow information...
To explore the evolution law of rotor vortex and aeroacoustic characteristics during helicopter roll maneuver flight, numerical simulations were conducted in different rates based on high-precision computational fluid dynamics method Ffowcs Williams-Hawkings equation. Initially, we verified collective pitch increased test blade/vortex interaction (BVI) cases. The comparison results show that constructed can capture aerodynamic transient maneuvering states has reliable predictive capability...
A new numerical method for predicting ice accretion on helicopter rotors is established. First, the orthogonal and body-fitted grids are generated around rotor blade, computational fluid dynamics flowfield of established by solving unsteady Reynolds-averaged Navier–Stokes equations. Based Eulerian approach, conservation equations mass momentum solved to obtain droplet properties. Then, a three-dimensional icing model considering influences centrifugal force, movement water film, variation...
The effects of synthetic jet control on unsteady dynamic stall over rotor airfoil are investigated numerically. A moving-embedded grid method and an Unsteady Reynolds Averaged Navier-Stokes (URANS) solver coupled with k-ω Shear Stress Transport (SST) turbulence model established for predicting the complex flowfields oscillatory under control. Additionally, a velocity boundary condition modeled by sinusoidal function has been developed to fulfill perturbation effect periodic jet. validity...
In order to calculate the unsteady aerodynamic characteristics of a tilt-rotor in conversion mode, virtual blade model (VBM) and an real (RBM) are established respectively. A new multi-layer moving-embedded grid technique is proposed reduce numerical dissipation wake mode. this method, system generated abound rotor accounts for rigid motions, searching scheme named adaptive inverse map (AIM) search corresponding donor elements present translate information among different computational...
Numerical simulations are performed to investigate the effects of synthetic jet control on separation and stall over rotor airfoils. The preconditioned unsteady Reynolds-averaged Navier–Stokes equations coupled with a k − ω shear stream transport turbulence model employed accomplish flowfield simulation airfoils under control. Additionally, velocity boundary condition modeled by sinusoidal function is developed fulfill perturbation effect periodic jets. validity present CFD procedure...
This paper proposes a robust and accurate implicit direct discontinuous Galerkin (DDG) method for simulating laminar turbulent flows. The Reynolds averaged Navier–Stokes (RANS) equations coupled with negative Spalart–Allmaras (SA) turbulence model are solved by using GMRES LU-SGS preconditioner to improve the convergence efficiency. A distinguished feature of this is that exact Jacobian matrix, derived analytically from Harten-Lax-van Leer-Contact convective flux accompanied DDG viscous SA...
The aerodynamic performance analysis and blade planform design of a coaxial rigid rotor in forward flight were carried out utilizing CFD solver CLORNS. Firstly, the flow field characteristics analyzed. Shock-induced separation occurs at advancing side tip severe reverse retreating root. Then, influence geometrical parameters on was investigated. Results show that swept-back could reduce compressibility drag elliptic shape optimize airload distribution high advance ratio flights. A kind...
In order to alleviate the dynamic stall effects in helicopter rotor, sequential quadratic programming (SQP) method is employed optimize characteristics of airfoil under conditions based on SC1095 airfoil. The geometry parameterized by class-shape-transformation (CST) method, and C-topology body-fitted mesh then automatically generated around solving Poisson equations. Based grid generation technology, unsteady Reynolds-averaged Navier-Stokes (RANS) equations are chosen as governing for...
Based on computational fluid dynamics (CFD) method, electromagnetic high-frequency method and surrogate model optimization techniques, an integration design about aerodynamic/stealth has been established for helicopter rotor. The developed is composed of three modules: integrated grids generation (the moving-embedded CFD solver the blade radar cross section (RCS) are generated by solving Poisson equations folding approach), aerodynamic characteristics simulated based upon Navier–Stokes...
A promising strategy of synthetic jet arrays (SJA) control for NACA0021 airfoil in preventing flow separation and delaying stall is investigated. Through aerodynamic forces, flowfield velocity profiles measurements, it indicates that the (SJ) could enlarge mixing shear layer then enhance stability boundary layer, resulting scope reduction zone. Furthermore, effects dual positioned at 15%c (Actuator 1) 40%c 2) respectively are systematically investigated with different parameters, such as two...