scholarly journals Estimation of Stability Parameters for Wide Body Aircraft Using Computational Techniques

2021 ◽  
Vol 11 (5) ◽  
pp. 2087
Author(s):  
Muhammad Ahmad ◽  
Zukhruf Liaqat Hussain ◽  
Syed Irtiza Ali Shah ◽  
Taimur Ali Shams
Keyword(s):  
Stability Control ◽  
Geometric Parameters ◽  
Control Surface ◽  
Complete Analysis ◽  
Computational Techniques ◽  
Control Analysis ◽  
Stability Parameters ◽  
Stability And Control ◽  
And Control ◽  
Control Coefficients

In this paper, we present the procedure of estimating the aerodynamic coefficients for a commercial aviation aircraft from geometric parameters at low-cruise-flight conditions using US DATCOM (United States Data Compendium) and XFLR software. The purpose of this research was to compare the stability parameters from both pieces of software to determine the efficacy of software solution for a wide-body aircraft at the stated flight conditions. During the initial phase of this project, the geometric parameters were acquired from established literature. In the next phase, stability and control coefficients of the aircraft were estimated using both pieces of software in parallel. Results obtained from both pieces of software were compared for any differences and the both pieces of software were validated with analytical correlations as presented in literature. The plots of various parameters with variations of the angle of attack or control surface deflection have also been obtained and presented. The differences between the software solutions and the analytical results can be associated with approximations of techniques used in software (the vortex lattice method is the background theory used in both DATCOM and XFLR). Additionally, from the results, it can be concluded that XFLR is more reliable than DATCOM for longitudinal, directional, and lateral stability/control coefficients. Analyses of a Boeing 747-200 (a wide-body commercial airliner) in DATCOM and XFLR for complete stability/control analysis including all modes in the longitudinal and lateral directions have been presented. DATCOM already has a sample analysis of a previous version of the Boeing 737; however, the Boeing 747-200 is much larger than the former, and complete analysis was, therefore, felt necessary to study its aerodynamics characteristics. Furthermore, in this research, it was concluded that XFLR is more reliable for various categories of aircraft alike in terms of general stability and control coefficients, and hence many aircraft can be dependably modeled and analyzed in this software.

Investigations on stability and control characteristics of a CS-VLA certified aircraft using wind tunnel test data

2016 ◽  
Vol 230 (14) ◽  
pp. 2728-2743 ◽  
Author(s):  
Nhu Van Nguyen ◽  
Maxim Tyan ◽  
Jae-Woo Lee ◽  
Sangho Kim
Keyword(s):  
Wind Tunnel ◽  
Test Data ◽  
Wind Tunnel Test ◽  
Stability Control ◽  
Scale Model ◽  
Control Analysis ◽  
Design Review ◽  
Stability And Control ◽  
The Stability ◽  
And Control

The stability and control characteristics using a wind tunnel test data process are proposed and developed to investigate the stability and control characteristics of a CS-VLA certified aircraft and to comply with the CS-VLA subpart B at the preliminary design review (PDR) and critical design review (CDR) stage. The aerodynamic characteristics of a 20% scale model are provided and investigated with clean, rudder, aileron, elevator, and winglet effects. The Mach and Reynolds correction methods are proposed to correct the aerodynamics of the scale model for stability and control analysis to obtain more reliable and accurate results of the full-scale model. The aerodynamic inputs and moment of inertia (MOI) comparison between the PDR and CDR stage show good agreement in the trends of stability and control derivatives. The CDR analysis results with the corrected wind tunnel test data and accurate MOI are investigated with respect to the longitudinal and lateral stability, control, and handling qualities to comply with the CS-VLA 173, CS-VLA 177, and CS-VLA 181 for finalizing the configuration in the CDR stage.

Modelling the flight dynamics of the hang glider

2005 ◽  
Vol 109 (1102) ◽  
pp. I-XX ◽  
Author(s):  
M. V. Cook ◽  
M. Spottiswoode
Keyword(s):  
Complex Geometry ◽  
Equations Of Motion ◽  
Linear Equations ◽  
Flight Dynamics ◽  
Control Analysis ◽  
Stability Margins ◽  
Stability And Control ◽  
Centre Of Gravity ◽  
Weight Shift ◽  
And Control

AbstractThe development of the non-linear equations of motion for the hang glider from first principles is described, including the complex geometry of control by pilot ‘weight shift’. By making appropriate assumptions the linearised small perturbation equations are derived for the purposes of stability and control analysis. The mathematical development shows that control is effected not by pilot weight shift, but by centre of gravity shift and that lateral-directional control by this means is weak, and is accompanied by significant instantaneous adverse response.The development of a comprehensive semi-empirical mathematical model of the flexible wing aerodynamics is described. In particular, the modelling attempts to quantify camber and twist dependencies. The performance of the model is shown to compare satisfactorily with measured hang glider wing data obtained in earlier full scale experiments. The mathematical aerodynamic model is then used to estimate the hang glider stability and control derivatives over the speed envelope for substitution into the linearised equations of motion.Solution of the equations of motion is illustrated and the flight dynamics of the typical hang glider are described. In particular, the dynamic stability properties are very similar to those of a conventional aeroplane, but the predicted lateral directional stability margins are significantly larger. The depth of mathematical modelling employed enables the differences to be explained satisfactorily. The unique control properties of the hang glider are described in some detail. Pitch and roll control of the hang glider is an aerodynamic phenomenon and results from the pilot adjusting his position relative to the wing in order to generate out of trim aerodynamic control moments about the centre of gravity. Maximum control moments are limited by hang glider geometry which is dependent on the length of the pilot‘s arm. The pilot does not generate control moments directly by shifting his weight relative to the wing. The modelling thus described would seem to give a plausible description of the flight dynamics of the hang glider.

Stability and Control Analysis of a Scooter

2003 ◽  
Author(s):  
S. Karthikeyan ◽  
M. Dighole ◽  
T. S. Nellainayagam ◽  
R. Venkatesan
Keyword(s):  
Control Analysis ◽  
Stability And Control ◽  
And Control

scholarly journals Vehicle yaw rate simulation and control based on single-track model

2021 ◽  
Vol 10 (1) ◽  
pp. 019-029
Author(s):  
Abdussalam Ali Ahmed ◽  
Faraj Ahmed Elzarook Barood ◽  
Munir S. Khalifa
Keyword(s):  
Control Method ◽  
Stability Control ◽  
Network Control ◽  
Control Analysis ◽  
Control Methods ◽  
Single Track ◽  
Linear Quadratic ◽  
Yaw Rate ◽  
Driving Conditions ◽  
And Control

When designing a vehicle, the most important variable that should be taken into account is the vehicle yaw rate, it represents an important indication of the vehicle’s stability and control. This paper aims to demonstrate how to simulate and control the yaw rate of a vehicle using two control methods, the first is the Linear Quadratic control method (LQR) and the other one is neural network control. The classical single-track model is prominently used for yaw stability control analysis. One driving conditions performed is the steering input; the steering input in this work is set as step steering angle and a lane change manoeuvre. Simulation results showed that both control methods used produced good and convergent performance results for the vehicle under different driving conditions.

Paper 2. Problems and Requirements of Directional Stability, Control and Manoeuvrability; High-Speed Craft

1972 ◽  
Vol 14 (7) ◽  
pp. 6-13
Author(s):  
M. C. Eames
Keyword(s):  
High Speed ◽  
Stability Control ◽  
Paper Briefly ◽  
Planing Craft ◽  
Stability And Control ◽  
Directional Stability ◽  
Air Cushion ◽  
And Control ◽  
Air Cushion Vehicles

The problems of stability and control of high-speed craft are somewhat different for the various vehicle types. The first part of this paper briefly compares characteristics of air-cushion vehicles and planing craft. This is followed by a more detailed discussion of the problems and requirements of hydrofoil craft.

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