Nonlinear Aeroelastic Analysis of a Wing with Control Surface Freeplay in Subsonic/Transonic Regions

2007 ◽  
Vol 35 (4) ◽  
pp. 295-301
Keyword(s):  
Control Surface ◽  
Aeroelastic Analysis

Linear and Nonlinear Aeroelastic Analysis of Fighter-Type Wing with Control Surface

2002 ◽  
Vol 39 (4) ◽  
pp. 697-708 ◽  
Author(s):  
Jae-Sung Bae ◽  
Seung-Man Yang ◽  
In Lee
Keyword(s):  
Control Surface ◽  
Aeroelastic Analysis ◽  
Linear And Nonlinear

Stochastic Nonlinear Aeroelastic Analysis of a Swept Wing Based on Nastran

2013 ◽  
Vol 444-445 ◽  
pp. 738-742
Author(s):  
Yi Li ◽  
Jun Yang ◽  
Nan Chang
Keyword(s):  
Analytical Procedure ◽  
Risk Information ◽  
Free Play ◽  
Uncertain Parameter ◽  
Control Surface ◽  
Swept Wing ◽  
Aeroelastic Analysis

For both military and civil aircrafts are in service, there is always a variation of free play among the joint components of control due to wear. In fact, the variation of free play is an uncertain parameter. In this paper analytical procedure was developed basing on Nastran, which can quantify uncertainties in the complicated swept wing with control surface and gives the quantificational risk information about nonlinear aeroelstic stability in the practice.

A Morphing Wind Turbine Blade Control Surface

2011 ◽  
Author(s):  
Stephen Daynes ◽  
Paul M. Weaver
Keyword(s):  
Wind Turbine ◽  
Turbine Rotor ◽  
Control Surface ◽  
Aeroelastic Analysis ◽  
Load Carrying ◽  
Aerodynamic Control ◽  
Flap Design ◽  
Work Done ◽  
Blade Loads ◽  
Wind Turbine Rotor

The loads on wind turbine components are primarily from the blades. It is important to control these blade loads in order to avoid damaging the wind turbine. Rotor control technology is currently limited to controlling the rotor speed and the pitch of the blades. As blades increase in length it becomes less desirable to pitch the entire blade as a single rigid body, but instead there is a requirement to control loads more precisely along the length of the blade. This can be achieved with aerodynamic control devices such as flaps. Morphing technologies are good candidates for wind turbine flaps because they have the potential to create structures that have the conflicting abilities of being load carrying, light-weight and shape adaptive. A morphing flap design with a highly anisotropic cellular structure is presented which is able to undergo large deflections and high strains without a large actuation penalty. An aeroelastic analysis couples the work done by aerodynamic loads on the flap, the flap strain energy and the required actuation work to change shape. The morphing flap is experimentally validated with a manufactured demonstrator and shown to have reduced actuation requirements compared to a conventional hinged flap.

Characterization of carbides in M50NiL

1991 ◽  
Vol 49 ◽  
pp. 606-607
Author(s):  
L. S. Lin ◽  
K. P. Gumz ◽  
A. V. Karg ◽  
C. C. Law
Keyword(s):  
Temperature Effects ◽  
Base Composition ◽  
Lattice Parameter ◽  
Control Surface ◽  
Carbide Formation ◽  
Particle Sizes ◽  
Low Carbon ◽  
Fee Structure ◽  
Heat Treated

Carbon and temperature effects on carbide formation in the carburized zone of M50NiL are of great importance because they can be used to control surface properties of bearings. A series of homogeneous alloys (with M50NiL as base composition) containing various levels of carbon in the range of 0.15% to 1.5% (in wt.%) and heat treated at temperatures between 650°C to 1100°C were selected for characterizations. Eleven samples were chosen for carbide characterization and chemical analysis and their identifications are listed in Table 1.Five different carbides consisting of M6C, M2C, M7C3 and M23C6 were found in all eleven samples examined as shown in Table 1. M6C carbides (with least carbon) were found to be the major carbide in low carbon alloys (<0.3% C) and their amounts decreased as the carbon content increased. In sample C (0.3% C), most particles (95%) encountered were M6C carbide with a particle sizes range between 0.05 to 0.25 um. The M6C carbide are enriched in both Mo and Fe and have a fee structure with lattice parameter a=1.105 nm (Figure 1).

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