Conceptualizing Active-Load-Alleviation: Impacts on Transport Category Aircraft Wing Structural Design

2016 ◽  
Author(s):  
Mathew Allyn ◽  
Timothy T. Takahashi
Keyword(s):  
Structural Design ◽  
Aircraft Wing ◽  
Active Load

scholarly journals STRUCTURE ANALYSIS AND MANUFACTURING OF WINGS TRAINER-5774

Vortex ◽  
2021 ◽  
Vol 1 (2) ◽  
pp. 107
Author(s):  
Suciari Dewi Triani ◽  
Moh Ardi Cahyono ◽  
Lazuardy Rahendra Pinandhita
Keyword(s):  
Remote Control ◽  
Structure Analysis ◽  
Structural Design ◽  
Manufacturing Process ◽  
Aircraft Wing ◽  
Margin Of Safety ◽  
Wing Structure ◽  
Aircraft Loads

Unmanned Aerial Vechicle (UAV) is one of the types an aircraft. Trainer is part of an airplane where the aircraft is controlled by a remote control for its flight. One of the things that must be considred in design an airplane is strength and and resistance of the wing structure in accepting distributed aircraft loads. In addition to the structural design and load, the material to be used can have an effect. The process is starting from modification of the aircraft wing using CATIA V5R20 which is then carried out analysis of the wing structure by being given the aircraft load using ANSYS 19. The largest structural value is in the Joiner section of 7,967 with manuvering load and smallest value is 0,026 on the Spar section. Margin of safety smallest value in the spar when its manuver. After analysis it is continued with the manufacturing process according to the design that has been made.

Optimum Design of Wing Structures With Multiple Frequency Constraints

1987 ◽  
Author(s):  
V. B. Venkayya ◽  
R. V. Grandhi
Keyword(s):  
Structural Design ◽  
Large Scale ◽  
Optimality Criterion ◽  
Multiple Frequency ◽  
Aircraft Wing ◽  
Design Problems ◽  
Frequency Constraints ◽  
Transport Aircraft ◽  
Scaling Procedure ◽  
Wing Structures

Abstract In this paper, design optimization of aircraft wing structures with multiple frequency constraints is considered. An optimality criterion algorithm along with a scaling procedure has been used. Large scale structural design problems were considered for demonstrating the reliability and efficiency of the algorithm. A simplified fighter wing, an intermediate complexity wing, and a large wing typical of a transport aircraft were considered as design examples. Design histories and the first few frequencies at the initial and final conditions are presented.

scholarly journals Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft

2021 ◽  
Vol 11 (5) ◽  
pp. 2439 ◽  
Author(s):  
Ignazio Dimino ◽  
Giovanni Andreutti ◽  
Frédéric Moens ◽  
Federico Fonte ◽  
Rosario Pecora ◽  
...  
Keyword(s):  
Fault Tolerant ◽  
Fuel Efficiency ◽  
Integrated Design ◽  
Design Parameters ◽  
Surface Geometry ◽  
Aircraft Wing ◽  
Novel Technologies ◽  
Active Load ◽  
Trade Offs ◽  
Control Surfaces

Aircraft winglets are well-established devices that improve aircraft fuel efficiency by enabling a higher lift over drag ratios and lower induced drag. Retrofitting winglets to existing aircraft also increases aircraft payload/range by the same order of the fuel burn savings, although the additional loads and moments imparted to the wing may impact structural interfaces, adding more weight to the wing. Winglet installation on aircraft wing influences numerous design parameters and requires a proper balance between aerodynamics and weight efficiency. Advanced dynamic aeroelastic analyses of the wing/winglet structure are also crucial for this assessment. Within the scope of the Clean Sky 2 REG IADP Airgreen 2 project, targeting novel technologies for next-generation regional aircraft, this paper deals with the integrated design of a full-scale morphing winglet for the purpose of improving aircraft aerodynamic efficiency in off-design flight conditions, lowering wing-bending moments due to maneuvers and increasing aircraft flight stability through morphing technology. A fault-tolerant morphing winglet architecture, based on two independent and asynchronous control surfaces with variable camber and differential settings, is presented. The system is designed to face different flight situations by a proper action on the movable control tabs. The potential for reducing wing and winglet loads by means of the winglet control surfaces is numerically assessed, along with the expected aerodynamic performance and the actuation systems’ integration in the winglet surface geometry. Such a device was designed by CIRA for regional aircraft installation, whereas the aerodynamic benefits and performance were estimated by ONERA on the natural laminar flow wing. An active load controller was developed by PoliMI and UniNA performed aeroelastic trade-offs and flutter calculations due to the coupling of winglet movable harmonics and aircraft wing bending and torsion.

scholarly journals New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis

2017 ◽  
Vol 65 (5) ◽  
pp. 741-750
Author(s):  
D. Gawel ◽  
M. Nowak ◽  
H. Hausa ◽  
R. Roszak
Keyword(s):  
Structural Design ◽  
Interaction Analysis ◽  
Load Case ◽  
Aircraft Wing ◽  
And Topology ◽  
Aeroelastic Analysis ◽  
Biomimetic Approach ◽  
Wing Structure ◽  
Multiple Load Case ◽  
Multiple Load

Abstract This paper presents a new biomimetic approach to the structural design. For the purpose of aircraft wing design the numerical environment combining simultaneous structural size, shape, and topology optimization based on aeroelastic analysis was developed. For the design of aircraft elements the optimization process must be treated as a multi-load case task, because during the fluid structure interaction analysis each step represents a different structural load case. Also, considering different angles of attack, during the CFD computation each result is considered. The method-specific features (such as domain independence, functional configurations during the process of optimization, and multiple load case solution implemented in the optimization scenario) enable the optimal structural form. To illustrate the algorithm functionality, the problem of determining the optimal internal wing structure was presented. The optimal internal wing structure resulting from aeroelastic computation with different angles of attack has been presented.

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