Lift Control on Pitching Wings Experiencing Gusts

2022 ◽  
Author(s):  
Ignacio Andreu Angulo ◽  
Holger Babinsky
Keyword(s):  
Lift Control

scholarly journals Adaptive Longitudinal Control of UAVs with Direct Lift Control

2016 ◽  
Vol 49 (1) ◽  
pp. 296-301 ◽  
Author(s):  
Ravi Jaiswal ◽  
Abhishek Shastry ◽  
Swati Swarnkar ◽  
Mangal Kothari
Keyword(s):  
Longitudinal Control ◽  
Lift Control

Lift Control Using MEMS-Based Moving Trailing-Edge Tabs

2002 ◽  
Author(s):  
C. P. van Dam ◽  
C. Bauer ◽  
D. T. Yen Nakafuji
Keyword(s):  
Lift Coefficient ◽  
Aerodynamic Characteristics ◽  
Trailing Edge ◽  
Aircraft Wings ◽  
Lifting Surface ◽  
Lifting Surfaces ◽  
Lift Control

Micro-electro-mechanical (MEM) translational tabs are introduced for active lift control on aircraft. These tabs are mounted near the trailing edge of lifting surfaces such as aircraft wings and tails, deploy approximately normal to the surface, and have a maximum deployment height on the order of one percent of the section chord. Deployment of the tab effectively changes the sectional camber, thereby changing the aerodynamic characteristics of a lifting surface. Tabs with said deployment height generate a change in the section lift coefficient of approximately ±0.3. The microtab design and the techniques used to fabricate and test the tabs are presented.

scholarly journals A VLSI implementation of elevator control based on finite state machine using Verilog HDL

2018 ◽  
Vol 7 (2.8) ◽  
pp. 92
Author(s):  
Naresh Lagadapati ◽  
Manoj Karri ◽  
Tejaswini Vaddineni ◽  
Sk Mahaboob Subhani ◽  
K Hari Kishore
Keyword(s):  
Finite State Machine ◽  
Control Variable ◽  
Vlsi Implementation ◽  
Verilog Hdl ◽  
Control Module ◽  
Control Framework ◽  
Finite State ◽  
Control Procedures ◽  
High Utilization ◽  
Lift Control

In this cutting edge period, lifts have turned into a basic piece of any business or open complex. It encourages the quicker development of individuals and gear between floors. The lift control framework is a standout amongst the most critical perspectives in hardware control module that are utilized as a part of car application. Normally lifts are intended for a particular building considering the fundamental factors, for example, the tallness of the building, the quantity of individuals venturing out to each floor and the normal times of high utilization. The lift framework is composed with various control procedures. This usage depends on FPGA, which can be utilized for a working with any number of floors, with the predetermined sources of info and yields. This controller can be executed for a lift with the required number of floors by just changing a control variable in the HDL code. This approach depends on a calculation which decreases the measure of calculation required, by concentrating just on the pertinent guidelines that enhances the execution of the gathering of lift framework.

Paper 20. Improvement of Control by Special Devices

1972 ◽  
Vol 14 (7) ◽  
pp. 150-154
Author(s):  
H. Ritter
Keyword(s):  
Large Angle ◽  
Leading Edge ◽  
Rotating Cylinder ◽  
Practical Significance ◽  
Trailing Edge ◽  
Stall Angle ◽  
Lift Control ◽  
And Control

The paper discusses hydrodynamic devices for improving manoeuvring and control. Two hydrodynamic concepts are shown to be of practical significance for large craft: control of hydrofoil lift independent of incidence, and deflection of the propulsion jet through a large angle by means of a simple hydrofoil. Lift control independent of incidence is illustrated by the jet flap and the trailing edge rotating cylinder. Improved deflection of the propeller slipstream involves extending the rudder stall angle, and it is shown how this may be achieved by fitting the rudder with a leading edge rotating cylinder.

scholarly journals Experimental lift control using fluidic jets on a model wind turbine

2018 ◽  
Vol 1037 ◽  
pp. 022014
Author(s):  
S Baleriola ◽  
A Leroy ◽  
S Loyer ◽  
Ph Devinant ◽  
S Aubrun
Keyword(s):  
Wind Turbine ◽  
Lift Control

Transonic equivalence rule: a nonlinear problem involving lift

1975 ◽  
Vol 72 (1) ◽  
pp. 161-187 ◽  
Author(s):  
H. K. Cheng ◽  
M. M. Hafez
Keyword(s):  
Transonic Flow ◽  
Line Source ◽  
Sectional Area ◽  
Small Disturbance ◽  
Cross Sectional ◽  
Outer Flow ◽  
Nonlinear Structure ◽  
First Order ◽  
Lift Control ◽  
Area Rule

The inviscid transonic flow past a thin wing having swept leading edges, with smooth lift and thickness distributions, is shown to possess an outer nonlinear structure determined principally by a line source and a line doublet. Three domains (the thickness-dominated, the intermediate, and the lift-dominated), representing different degrees of lift control of the outer flow, are identified; a transonic equivalence rule valid in all three domains is established. Except in one domain, departure from the Whitcomb-Oswatitsch area rule is significant; the equivalent body corresponding to the source effect has an increased cross-sectional area depending nonlinearly on the lift. This nonlinear lift contribution results from the second-order corrections to the inner (Jones) solution, but produces effects of first-order importance in the outer flow. Of interest is an afterbody effect dependent on the vortex drag, which is not accounted for by the classical transonic small-disturbance theory.

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