Description of High Lift Control Systems

2020 ◽  
Author(s):  
Keyword(s):  
Control Systems ◽  
High Lift ◽  
Lift Control

High lift control system design for a transport aircraft

2018 ◽  
Vol 48 (3) ◽  
pp. 289-298
Author(s):  
YongLiang DU ◽  
YaKui GAO
Keyword(s):  
Control System ◽  
System Design ◽  
Control System Design ◽  
High Lift ◽  
Transport Aircraft ◽  
Lift Control

scholarly journals Experimental Study of Flexible Skin Designs Between a Moving Wing Segment and a Fixed Wing Part on a Full Scale Demonstrator

2020 ◽  
Author(s):  
Martin Radestock ◽  
Johannes Riemenschneider ◽  
Alexander Falken ◽  
Johannes Achleitner
Keyword(s):  
Control Systems ◽  
Optical Measurement ◽  
Leading Edge ◽  
Full Scale ◽  
Smooth Transition ◽  
Plane Shear ◽  
High Lift ◽  
Local Skin ◽  
Flexible Skin ◽  
Triangular Design

Abstract Commercial aircraft today require efficient high-lift and control systems on the wings to reduce the drag in flight or decrease the take-off and landing speeds. Morphing mechanisms are one approach for improved high-lift systems. In most cases the objective function is an increased lift to drag ratio or the noise reduction. On closer examination control systems as well as morphing mechanisms are located in a certain wing segment. The transition between a moving wing part and the fixed wing is a step, which creates additional vortices. This segments the wing in span-wise direction and reduces the efficiency. A flexible skin between a moving and a fixed wing parts smooths the contour and minimize the efficiency reduction of the wing. A full scale demonstrator of a wing segment was manufactured with two flexible skin designs. The first subcomponent connects a morphing leading edge with a rib of the wing over a span of one meter. The skin is a material mix of ethylene-propylene-diene monomer (EPDM) rubber and fiberglass-reinforced plastic. The rubber is the basis of the skin and the glass-fiber is added as local skin stiffeners in the form of strips in chord-wise direction. The second subcomponent blends the aileron with a rib of the wing in a triangular design. The connection of three different hinges realizes a morphing triangle, which is loaded in an in-plane shear only state of stress in each aileron position. The core of the triangle is a 3D printed structure, which is free in shear. The covering skin is a combination of EPDM with carbon fibers oriented in +/−30° direction to obtain shear compliance and to resist the loads on the triangle. The deformation of each concept is identified at the demonstrator. Therefore, an optical measurement system scans the surface in the initial and deflected state. The required deformation precision of the concepts differs due to their design. The contour at the leading edge requires a certain shape over the span. The analysis of the skin buckling is one requirement at the transition triangle during the aileron motion. The experimental results show a smooth transition contour at the leading edge and no buckling effects at the triangle. The results can be used for the validation of simulation models. Furthermore, both skin concepts cover the gap between a moving wing segment and a fixed wing part. The elimination of steps in span-wise direction can improve the aero-acoustic behavior along the wing for future aircraft.

Application of Pulsed Blowing Technique in High-Lift Control Surface Design

2012 ◽  
Vol 482-484 ◽  
pp. 121-125
Author(s):  
Peng Wu ◽  
Xue Ying Deng ◽  
Yan Kui Wang
Keyword(s):  
Flow Separation ◽  
Deflection Angle ◽  
Leading Edge ◽  
Control Surface ◽  
Control Technique ◽  
High Lift ◽  
Surface Design ◽  
Aerodynamic Efficiency ◽  
Lift Control ◽  
Control Surfaces

Because the flight performance of aircraft is so dependent on aerodynamic efficiency of control surfaces, it is very important to eliminate the flow separation over the control surfaces at high deflection angle in order to keep the aircraft having good flight capability, especially for the modern aircraft with tailless aerodynamic configuration. A novel flow control technique to eliminate flow separation of control surface at high deflection angle and creat high lift increment by pulsed blowing at leading edge of control surface is discussed in this paper. The performance of lift enhancment of control surface which used this technique is investigated, and based on the zonal analysis of pulsed frequency, the control characteristic of this technique is also discussed.

Boeing 777 high lift control system

1993 ◽  
Vol 8 (8) ◽  
pp. 15-21 ◽  
Author(s):  
J. Rea
Keyword(s):  
Control System ◽  
High Lift ◽  
Lift Control

Evaluation of tunnel sidewall boundary-layer-control systems for high-lift airfoil testing

1991 ◽  
Author(s):  
K. PASCHAL ◽  
W. GOODMAN ◽  
R. MCGHEE ◽  
B. WALKER ◽  
PETER WILCOX
Keyword(s):  
Boundary Layer ◽  
Control Systems ◽  
Boundary Layer Control ◽  
High Lift ◽  
Layer Control

New tools for engine control systems development

1999 ◽  
Vol 23 (1) ◽  
pp. 109-116
Author(s):  
R Stobart
Keyword(s):  
Control Systems ◽  
Systems Development ◽  
Engine Control

Medical control systems

AccessScience ◽  
2015 ◽  
Keyword(s):  
Control Systems ◽  
Medical Control
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