scholarly journals Electrical Wing Prototype Anti Icing pada Pesawat Komersil

2020 ◽  
Vol 2 (2) ◽  
pp. 34-41
Author(s):  
Elfitra Desifatma
Keyword(s):  
Leading Edge ◽  
Control Unit ◽  
Heating Element ◽  
Commercial Aircraft ◽  
Aerodynamic Properties ◽  
Input Control

The accumulation of ice on the aircraft's wings can cause a decrease in the aerodynamic properties of the aircraft, increase in weight, and it is difficult to control the aircraft so that it affects aircraft safety. Icing handling on aircraft is growing. One of the newest systems being developed is electrical anti-icing. Therefore, the researcher designed a prototype of an anti-icing electrical wing on a commercial aircraft with advantages in terms of maintenance and lighter components. The purpose of making this prototype is to design an anti-icing electrical wing in the form of a prototype and can be used as an anti-icing. The prototype consists of three parts, namely input, control unit, and heating element. The heating element working system is by attaching the heating element to the surface of the wing, so when the tool is active through the controls, the heating element will work with an indication of the LED on. After testing the Prototype electrical anti-icing function that has been made, it can be used as a de-icing that removes icing that has already frozen on the leading edge.

scholarly journals Analysis and Design of a Leading Edge with Morphing Capabilities for the Wing of a Regional Aircraft—Gapless Chord- and Camber-Increase for High-Lift Performance

2021 ◽  
Vol 11 (6) ◽  
pp. 2752
Author(s):  
Conchin Contell Asins ◽  
Volker Landersheim ◽  
Dominik Laveuve ◽  
Seiji Adachi ◽  
Michael May ◽  
...  
Keyword(s):  
Leading Edge ◽  
Bird Strike ◽  
High Lift ◽  
Analysis And Design ◽  
Actuation System ◽  
Aerodynamic Properties ◽  
Reinforced Plastic ◽  
Stall Angle ◽  
Carbon Fibre Reinforced Plastic ◽  
Electromechanical Actuation

In order to contribute to achieving noise and emission reduction goals, Fraunhofer and Airbus deal with the development of a morphing leading edge (MLE) as a high lift device for aircraft. Within the European research program “Clean Sky 2”, a morphing leading edge with gapless chord- and camber-increase for high-lift performance was developed. The MLE is able to morph into two different aerofoils—one for cruise and one for take-off/landing, the latter increasing lift and stall angle over the former. The shape flexibility is realised by a carbon fibre reinforced plastic (CFRP) skin optimised for bending and a sliding contact at the bottom. The material is selected in terms of type, thickness, and lay-up including ply-wise fibre orientation based on numerical simulation and material tests. The MLE is driven by an internal electromechanical actuation system. Load introduction into the skin is realised by span-wise stringers, which require specific stiffness and thermal expansion properties for this task. To avoid the penetration of a bird into the front spar of the wing in case of bird strike, a bird strike protection structure is proposed and analysed. In this paper, the designed MLE including aerodynamic properties, composite skin structure, actuation system, and bird strike behaviour is described and analysed.

scholarly journals Beyond analogy: A model of bioinspiration for creative design

2016 ◽  
Vol 30 (2) ◽  
pp. 159-170 ◽  
Author(s):  
Camila Freitas Salgueiredo ◽  
Armand Hatchuel
Keyword(s):  
Design Process ◽  
Design Theory ◽  
Leading Edge ◽  
Knowledge Bases ◽  
Biologically Inspired ◽  
Concept Knowledge ◽  
Bioinspired Design ◽  
Aerodynamic Properties ◽  
Biologically Inspired Design ◽  
The Impact

AbstractIs biologically inspired design only an analogical transfer from biology to engineering? Actually, nature does not always bring “hands-on” solutions that can be analogically applied in classic engineering. Then, what are the different operations that are involved in the bioinspiration process and what are the conditions allowing this process to produce a bioinspired design? In this paper, we model the whole design process in which bioinspiration is only one element. To build this model, we use a general design theory, concept–knowledge theory, because it allows one to capture analogy as well as all other knowledge changes that lead to the design of a bioinspired solution. We ground this model on well-described examples of biologically inspired designs available in the scientific literature. These examples include Flectofin®, a hingeless flapping mechanism conceived for façade shading, and WhalePower technology, the introduction of bumps on the leading edge of airfoils to improve aerodynamic properties. Our modeling disentangles the analogical aspects of the biologically inspired design process, and highlights the expansions occurring in both knowledge bases, scientific (nonbiological) and biological, as well as the impact of these expansions in the generation of new concepts (concept partitioning). This model also shows that bioinspired design requires a special form of collaboration between engineers and biologists. Contrasting with the classic one-way transfer between biology and engineering that is assumed in the literature, the concept–knowledge framework shows that these collaborations must be “mutually inspirational” because both biological and engineering knowledge expansions are needed to reach a novel solution.

scholarly journals Features of owl wings that promote silent flight

2017 ◽  
Vol 7 (1) ◽  
pp. 20160078 ◽  
Author(s):  
Hermann Wagner ◽  
Matthias Weger ◽  
Michael Klaas ◽  
Wolfgang Schröder
Keyword(s):  
Noise Reduction ◽  
Leading Edge ◽  
Aerodynamic Performance ◽  
Wing Loading ◽  
Trailing Edge ◽  
Future Directions ◽  
Trailing Edge Noise ◽  
Aerodynamic Properties ◽  
Morphological Adaptations ◽  
Noise Production

Owls are an order of birds of prey that are known for the development of a silent flight. We review here the morphological adaptations of owls leading to silent flight and discuss also aerodynamic properties of owl wings. We start with early observations (until 2005), and then turn to recent advances. The large wings of these birds, resulting in low wing loading and a low aspect ratio, contribute to noise reduction by allowing slow flight. The serrations on the leading edge of the wing and the velvet-like surface have an effect on noise reduction and also lead to an improvement of aerodynamic performance. The fringes at the inner feather vanes reduce noise by gliding into the grooves at the lower wing surface that are formed by barb shafts. The fringed trailing edge of the wing has been shown to reduce trailing edge noise. These adaptations to silent flight have been an inspiration for biologists and engineers for the development of devices with reduced noise production. Today several biomimetic applications such as a serrated pantograph or a fringed ventilator are available. Finally, we discuss unresolved questions and possible future directions.

scholarly journals Computational Evaluation of Control Surfaces Aerodynamics for a Mid-Range Commercial Aircraft

Aerospace ◽  
2020 ◽  
Vol 7 (10) ◽  
pp. 139
Author(s):  
Nunzio Natale ◽  
Teresa Salomone ◽  
Giuliano De Stefano ◽  
Antonio Piccolo
Keyword(s):  
Flight Control ◽  
Realistic Model ◽  
Navier Stokes ◽  
Flight Control System ◽  
Commercial Aircraft ◽  
Virtual Experiments ◽  
Computational Evaluation ◽  
Aerodynamic Properties ◽  
The Mean ◽  
Control Surfaces

Computational fluid dynamics is employed to predict the aerodynamic properties of the prototypical trailing-edge control surfaces for a small, regional transport, commercial aircraft. The virtual experiments are performed at operational flight conditions, by resolving the mean turbulent flow field around a realistic model of the whole aircraft. The Reynolds-averaged Navier–Stokes approach is used, where the governing equations are solved with a finite volume-based numerical method. The effectiveness of the flight control system, during a hypothetical conceptual pre-design phase, is studied by conducting simulations at different angles of deflection, and examining the variation of the aerodynamic loading coefficients. The proposed computational modeling approach is verified to have good practical potential, also compared with reference industrial data provided by the Leonardo Aircraft Company.

Influence of Geometric Imperfections on Aerodynamic and Aeroelastic Behavior of a Compressor Blisk

2017 ◽  
Author(s):  
Christian Keller ◽  
Andreas Kellersmann ◽  
Jens Friedrichs ◽  
Joerg R. Seume
Keyword(s):  
High Pressure ◽  
Numerical Study ◽  
Leading Edge ◽  
Mode Shapes ◽  
Local Pressure ◽  
Torsional Mode ◽  
Local Flow ◽  
Geometric Imperfections ◽  
Geometrical Properties ◽  
Aerodynamic Properties

Impacts of foreign objects can cause cracks and dents in airfoils, especially in the leading edge. The regeneration of high-pressure compressors blisks with current repair methods is often restricted to a local blending of these edges. This can cause significant changes in the airfoils’ geometrical properties, which in turn influence their aerodynamic and aeroelastic characteristics. Changes at the leading edge have a particularly strong influence on the airfoils’ aerodynamic properties. In order to be able to make an informed decision about if and how a repair should be performed, consequences have to be predicted in advance. To investigate their influence on the aerodynamic and aeroelastic behavior, typical blend repairs are applied to the geometry of a blisk in a 1.5-stage research axial compressor [1], which are representative in shape and size. Blisks (Blade-Integrated-diSK) are function integrated components, which are expected to have a high life span due to significant costs in design and production. Similar modifications are implemented at different radial heights of the blades, in order to investigate the influence of location and penetration depth of blend repairs. It is assured that only the blend repair region is modified while the rest of the blade stays in the original shape. Thus, a realistic change of the geometry is given. The numerical study presented here deals with the influence of geometric imperfections, blend repairs in particular, on the aerodynamic and aeroelastic behavior of the high pressure compressors blisks. Results show that blend repairs have an influence on the local pressure distribution as well as on the local flow turning. Even though the leading edge is reshaped during repair, performance degradation can be observed. Furthermore, the working range of the compressor stage is influenced by the blend-repairs, which is of great importance for safe operation. Finally, the local changes in aerodynamics and blade deformation influence the aeroelastic behavior. This influence depends on the investigated mode shape and the location of the modification. The closer the modification is located towards the tip, the more pronounced are the shifts in aerodynamic damping and aerodynamic stiffness. Low torsional mode shapes display the highest sensitivity to the modifications.

scholarly journals A Sensitivity Analysis of the Damage Behavior of a Leading-Edge Subject to Bird Strike

2020 ◽  
Vol 10 (22) ◽  
pp. 8187
Author(s):  
Francesco Di Caprio ◽  
Andrea Sellitto ◽  
Salvatore Saputo ◽  
Michele Guida ◽  
Aniello Riccio
Keyword(s):  
Sensitivity Analysis ◽  
Structural Response ◽  
Leading Edge ◽  
Design Parameters ◽  
Bird Strike ◽  
Commercial Aircraft ◽  
Output Data ◽  
Plastic Deformations ◽  
Maximum Deformation ◽  
Energy Dissipated

This paper aims to investigate the crashworthiness capability of a commercial aircraft metallic sandwich leading edge, subjected to bird strike events. A sensitivity analysis is presented, aimed to assess the influence of the skin parameters (inner and outer faces and core thicknesses) on the leading-edge crashworthiness and to determine, among the configurations able to withstand a bird strike event, the best compromise in terms of weight and structural performances. In order to easily manage the design parameters and the output data, the ModeFrontier code was used in conjunction with the FE code Abaqus/Explicit. A dedicated python routine was developed to define a fully parametric simplified leading-edge model. To fulfill the aerodynamic requirements, the external surfaces were considered fixed during the sensitivity analysis, and, thus, only the internal leading edge’s components were modified to study their influence on the structural response. The total mass of the model, the maximum deformation and the energy dissipated due to material failure and the plastic deformations were monitored and used to compare and assess the behavior of each configuration.

scholarly journals Optoelectronic complex for express laser diodes lifetime prediction

2019 ◽  
Vol 220 ◽  
pp. 02002
Author(s):  
Vladimir Bliznyuk ◽  
Alexey Dolgov ◽  
Vasiliy Parshin ◽  
Alexey Rzhanov ◽  
Olga Semenova ◽  
...  
Keyword(s):  
Spectral Characteristics ◽  
Laser Diodes ◽  
Control Unit ◽  
Single Mode ◽  
Lifetime Prediction ◽  
Measurement Unit ◽  
Spectral Radiation ◽  
Single Mode Laser ◽  
Initial Stage ◽  
Input Control

This paper presents the optoelectronic complex, which provides both preparations for carrying out an express lifetime prediction of edge emitted strip single-mode laser diodes. It is shown that for this purpose the complex should consist of four operational units: an input control unit; a spectral radiation characteristics measurement unit; a laser lifetime forecasting unit and automatic processing hardware unit. The use of this complex makes it possible to predict the lifetime of a laser diode according to their spectral characteristics at the initial stage of its operation.

Path instabilities of streamlined bodies

2019 ◽  
Vol 864 ◽  
pp. 286-302
Author(s):  
Thibault Guillet ◽  
Martin Coux ◽  
David Quéré ◽  
Christophe Clanet
Keyword(s):  
Vertical Velocity ◽  
Initial Velocity ◽  
Equations Of Motion ◽  
Leading Edge ◽  
Centre Of Mass ◽  
Low Velocity ◽  
Diving Depth ◽  
Aerodynamic Properties ◽  
Different Types ◽  
Path Instabilities

We study the trajectory and the maximum diving depth of floating axisymmetric streamlined bodies impacting water with a vertical velocity. Three different types of underwater trajectory can be observed. For a centre of mass of the projectile located close to its leading edge, the trajectory is either straight at low velocity or y-shaped at high velocity. When the centre of mass is far from the leading edge, the trajectory has a U-shape, independent of the initial velocity. We first characterize experimentally the aerodynamic properties of the projectile and then solve the equations of motion to recover the three types of trajectories. We finally discuss the transitions between the different regimes.

scholarly journals Effect of a Slat Arm Door on the Wing Efficiency of a Commercial Aircraft.

2021 ◽  
Author(s):  
Sharman Perera
Keyword(s):  
Residence Time ◽  
Coming Out ◽  
Cfd Simulation ◽  
Leading Edge ◽  
Aerodynamic Performance ◽  
Cfd Analysis ◽  
Inert Particle ◽  
Commercial Aircraft ◽  
Local Flow ◽  
Closed Model

The objective of this thesis is to determine the influence of a slat arm door on the aerodynamic performance of a wing of a commercial aircraft during it's take off and landing configurations using CFD simulation. The slats are extended forward by extendable arms coming out from the leading edge of the wing after the slat arm is deployed. CFD analysis of wing and slat configuration of the aircraft showed that the removal of this slat door at higher angle of attacks increased the drag by 0.88%, reduced the lift by 1.29%, increased the inert particle residence time inside the slat door compartment by 200.00% and increased the local flow separation area on the top surface of the wing by 42.81% with reference to the closed model.

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