Review of Numerical Simulations on Aircraft Dynamic Stability Derivatives

Mi, Baigang; Li, Mingguang

doi:10.1007/s11831-019-09370-8

Cited by 14 publications

(10 citation statements)

References 51 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Translation acceleration derivative can be obtained either by flight tests, wind tunnel testing or computational fluid dynamic analysis, refer [57]. Wind tunnel testing for determination of translational acceleration derivatives is time consuming and a very costly solution.…”

Section: Proposed 6-degree Of Freedom Model With Inclusion Of Admentioning

confidence: 99%

“…Several methods exist for the evaluation of aircraft rate and acceleration derivatives [64] and [57]. Potential solvers is one way which solve Laplace equation valid for inviscid, incompressible and irrotational flow [65].…”

Section: B Rate Derivativesmentioning

confidence: 99%

“…Further, in this research rates and acceleration derivatives were estimated using potential flow solvers which presented errors in comparison with analytical results. It is recommended, that CFD analysis may be carried out to determine exact values of rate and acceleration derivatives for FWMAV by adopting new CFD methods as proposed in [63] and [57].…”

Section: Recommendationsmentioning

confidence: 99%

See 2 more Smart Citations

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

et al. 2020

View full text Add to dashboard Cite

In this research effect of propeller induced flow on aerodynamic characteristics of low aspect ratio flying wing micro aerial vehicle has been investigated experimentally in subsonic wind tunnel. Left turning tendencies of right-handed propellers have been discussed in literature, but not much work has been done to quantify them. In this research, we have quantified these tendencies as a change in aerodynamic coefficient with a change in advance ratio at a longitudinal trim angle of attack using subsonic wind tunnel. For experimental testing, three fixed pitch propeller diameters (5 inch, 6 inch and 7 inch), three propeller rotational speeds (7800, 10800 and 12300 RPMs) and three wind tunnel speeds (10, 15 and 20 m/s) have been considered to form up 27 advance ratios. Additionally, wind tunnel tests of 9 wind mill cases were conducted and considered as baseline. Experimental uncertainty assessment for measurement of forces and moments was carried out before conduct of wind tunnel tests. Large variation in lift, drag, yawing moment and rolling moment was captured at low advance ratios, which indicated their significance at high propeller rotational speeds and large propeller diameters. Side force and pitching moment did not reflect any significant change. L D at trim point was found a nonlinear function of propeller diameter to wingspan ratio D b , and propeller rotational speed. Rate and control derivatives were obtained using unsteady vortex lattice method with propeller induced flow effect modeled by Helical Vortex Modeling approach. In this research, we have proposed improved 6-DOF equations of motion, with a contribution of advance ratio J. It is concluded, that propeller induced flow effects have a significant contribution in flight dynamic modeling for vehicles with large propeller diameter to wingspan ratio, D b of 22% or more. INDEX TERMS Advance ratio, aerodynamic characteristics, flying wing micro aerial vehicle, Propeller induced flow, , wind tunnel testing, 6DOF Modeling

show abstract

Section: Proposed 6-degree Of Freedom Model With Inclusion Of Admentioning

confidence: 99%

Section: B Rate Derivativesmentioning

confidence: 99%

Section: Recommendationsmentioning

confidence: 99%

See 1 more Smart Citation

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

et al. 2020

View full text Add to dashboard Cite

show abstract

“…Since Bryan's introduction in 1911, the stability derivatives have been considered the basis for modeling the aerodynamic loads in the equations of motion of aerodynamic systems [19]. Different applications of stability derivatives include linearization of the model for a steady (otherwise with small perturbations) flight to describe the vehicle's dynamic stability, control system design, trajectory design, aerodynamic shape optimization and design and the development of flight simulators [20].…”

Section: Introductionmentioning

confidence: 99%

Stability Derivatives of Various Lighter-than-Air Vehicles: A CFD-Based Comparative Study

Anoop

Velamati

Janardhanan

et al. 2022

Drones

View full text Add to dashboard Cite

An aerostat with a single tether is proposed for the application of wind measurements at low altitudes. In the current study, the aerodynamic model parameters (stability derivatives) of the aerostat are investigated based on a CFD-based approach. The static, as well as the dynamic stability derivatives of the aerostats are presented. The calculation of the dynamic stability derivatives involves the simulation of the oscillations of the aerostats in their axial direction (surge), the vertical direction (heave) and angular motions with respect to the lateral direction (pitch). A forced sinusoidal oscillation is used for the simulation of the aerostat, and one stable period of oscillation is taken for the derivatives’ extraction. Four different aerostats are considered for the current study with four different angles of attack. The Zhiyuan aerostat, HAA aerostat, NPL aerostat and GNVR aerostat are the aerostats considered for this study. The stability derivative results obtained for the four aerostats are analyzed and compared with respect to their geometrical features. From the static aerodynamic characteristics, the Zhiyuan aerostat shows better performance than the other aerostats in terms of the lift–drag ratio. The dynamic stability derivatives of the Zhiyuan aerostat suggest its application as the proposed low-altitude wind measurement system.

show abstract

“…The dynamic aerodynamic characteristics of an aircraft originate from the motion of the aircraft affected by various factors. One of the most important concepts is dynamic stability [18][19][20][21][22][23][24], which refers to the damping moment during the movement of the aircraft after disturbance and finally makes the object return to the original equilibrium state. It studies the time response history of the disturbed movement of the object.…”

Section: Introductionmentioning

confidence: 99%

A New Aerodynamic Optimization Method with the Consideration of Dynamic Stability

Wang

2021

International Journal of Aerospace Engineering

Self Cite

View full text Add to dashboard Cite

Dynamic stability is significantly important for flying quality evaluation and control system design of the advanced aircraft, and it should be considered in the initial aerodynamic design process. However, most of the conventional aerodynamic optimizations only focus on static performances and the dynamic motion has never been included. In this study, a new optimization method considering both dynamic stability and general lift-to-drag ratio performance has been developed. First, the longitudinal combined dynamic derivative based on the small amplitude oscillation method is calculated. Then, combined with the PSO (particle swarm optimization) algorithm, a dynamic stability derivative that must not be decreased is added to the constraints of optimization and the lift-drag ratio is chosen as the optimization objective. Finally, a new aerodynamic optimization method can be built. We take NACA0012 as an example to validate this method. The results show that the dynamic derivative calculation method is effective and conventional optimization design can significantly improve the lift-drag ratio. However, the dynamic stability is enormously changed at the same time. By contrast, the new optimization method can improve the lift-drag performance while maintaining the dynamic stability.

show abstract

Review of Numerical Simulations on Aircraft Dynamic Stability Derivatives

Cited by 14 publications

References 51 publications

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

Stability Derivatives of Various Lighter-than-Air Vehicles: A CFD-Based Comparative Study

A New Aerodynamic Optimization Method with the Consideration of Dynamic Stability

Contact Info

Product

Resources

About