Static aeroelasticity

1995 ◽  
pp. 3-53 ◽  
Author(s):  
Edward F. Crawley ◽  
Howard C. Curtiss ◽  
David A. Peters ◽  
Robert H. Scanlan ◽  
Fernando Sisto
Keyword(s):  
Static Aeroelasticity

Assessment of flight dynamic and static aeroelastic behaviors for jet transport aircraft subjected to instantaneous high g-loads

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Yonghu Wang ◽  
Ray C. Chang ◽  
Wei Jiang
Keyword(s):  
Numerical Approach ◽  
Future Research ◽  
Inspection Method ◽  
Content Type ◽  
Flight Data ◽  
Transport Aircraft ◽  
Different Types ◽  
Static Aeroelasticity ◽  
Safety Operation ◽  
Structural Inspection

Purpose The purpose of this paper is to present a quick inspection method based on the post-flight data to examine static aeroelastic behavior for transport aircraft subjected to instantaneous high g-loads. Design/methodology/approach In the present study, the numerical approach of static aeroelasticity and two verified cases will be presented. The non-linear unsteady aerodynamic models are established through flight data mining and the fuzzy-logic modeling of artificial intelligence techniques based on post-flight data. The first and second derivatives of flight dynamic and static aeroelastic behaviors, respectively, are then estimated by using these aerodynamic models. Findings The flight dynamic and static aeroelastic behaviors with instantaneous high g-load for the two transports will be analyzed and make a comparison study. The circumstance of turbulence encounter of the new twin-jet is much serious than that of four-jet transport aircraft, but the characteristic of stability and controllability for the new twin-jet is better than those of the four-jet transport aircraft; the new twin-jet transport is also shown to have very small aeroelastic effects. The static aeroelastic behaviors for the two different types can be assessed by using this method. Practical implications As the present study uses the flight data stored in a quick access recorder, an intrusive structural inspection of the post-flight can be avoided. A tentative conclusion is to prove that this method can be adapted to examine the static aeroelastic effects for transport aircraft of different weights, different sizes and different service years in tracking static aeroelastic behavior of existing different types of aircraft. In future research, one can consider to have more issues of other types of aircraft with high composite structure weight. Originality/value This method can be used to assist airlines to monitor the variations of flight dynamic and static aeroelastic behaviors as a complementary tool for management to improve aviation safety, operation and operational efficiency.

Errata-Influence of Static Aeroelasticity onOblique Winged Aircraft

1974 ◽  
Vol 11 (12) ◽  
pp. 783-784
Author(s):  
Terrence A. Weisshaar
Keyword(s):  
Static Aeroelasticity

The Static Aeroelasticity of Slender Configurations

1963 ◽  
Vol 14 (1) ◽  
pp. 75-104 ◽  
Author(s):  
G. J. Hancock
Keyword(s):  
Static Stability ◽  
Aerodynamic Forces ◽  
Flexible Aircraft ◽  
The Past ◽  
Plate Models ◽  
Non Linear ◽  
The Future ◽  
Static Aeroelasticity ◽  
Definition Of ◽  
Image Position

SummaryThe validity and applicability of the static margin (stick fixed) Kn,where as defined by Gates and Lyon is shown to be restricted to the conventional flexible aircraft. Alternative suggestions for the definition of static margin are put forward which can be equally applied to the conventional flexible aircraft of the past and the integrated flexible aircraft of the future. Calculations have been carried out on simple slender plate models with both linear and non-linear aerodynamic forces to assess their static stability characteristics.

Static aeroelasticity and the flying wing, revisited

1974 ◽  
Vol 11 (11) ◽  
pp. 718-720 ◽  
Author(s):  
Terrence A. Weisshaar ◽  
Holt Ashley
Keyword(s):  
Static Aeroelasticity

The Static Aeroelastic Deformation of Slender Configurations

1961 ◽  
Vol 12 (3) ◽  
pp. 293-308 ◽  
Author(s):  
G. J. Hancock
Keyword(s):  
Critical Condition ◽  
Maximum Speed ◽  
Non Linear ◽  
Static Aeroelasticity ◽  
Control Forces ◽  
And Control ◽  
Simple Models

SummaryBy consideration of a series of simple models the static aeroelasticity of conventional aircraft is first discussed and then extended to the integrated configuration combining fuselage, wing and tail. It is shown that, on the basis of linear aerodynamics, a maximum speed exists at which control is possible. Overall deformations and control forces become large at speeds approaching this critical condition. Part II, to be published, contains calculations on slender plate aircraft including non-linear aerodynamics.

Influence of Static Aeroelasticity on Oblique Winged Aircraft

1974 ◽  
Vol 11 (4) ◽  
pp. 247-249 ◽  
Author(s):  
Terrence A. Weisshaar
Keyword(s):  
Static Aeroelasticity
Sign in / Sign up

Export Citation Format

Share Document