scholarly journals Design and Optimization of a Composite Canard Control Surface of an Advanced Fighter Aircraft under Static Loading

2015 ◽  
Vol 2 (1) ◽  
Author(s):  
Sachin Shrivastava ◽  
P.M. Mohite
Keyword(s):  
Static Loading ◽  
Fiber Composite ◽  
Design Procedure ◽  
Optimization Procedure ◽  
High Strength ◽  
Control Surface ◽  
Carbon Fiber Composite ◽  
Ferrous Alloys ◽  
Fighter Aircraft ◽  
Elitist Strategy

AbstractThe minimization of weight and maximization of payload is an ever challenging design procedure for air vehicles. The present study has been carried out with an objective to redesign control surface of an advanced all-metallic fighter aircraft. In this study, the structure made up of high strength aluminum, titanium and ferrous alloys has been attempted to replace by carbon fiber composite (CFC) skin, ribs and stiffeners. This study presents an approach towards development of a methodology for optimization of first-ply failure index (FI) in unidirectional fibrous laminates using Genetic-Algorithms (GA) under quasi-static loading. The GAs, by the application of its operators like reproduction, cross-over, mutation and elitist strategy, optimize the ply-orientations in laminates so as to have minimum FI of Tsai-Wu first-ply failure criterion. The GA optimization procedure has been implemented in MATLAB and interfaced with commercial software ABAQUS using python scripting. FI calculations have been carried out in ABAQUS with user material subroutine (UMAT). The GA's application gave reasonably well-optimized ply-orientations combination at a faster convergence rate. However, the final optimized sequence of ply-orientations is obtained by tweaking the sequences given by GA's based on industrial practices and experience, whenever needed. The present study of conversion of an all metallic structure to partial CFC structure has led to 12% of weight reduction. Therefore, the approach proposed here motivates designer to use CFC with a confidence.

scholarly journals Design and Optimization of Lug Bracket Assembly

2021 ◽  
Vol 13 (1) ◽  
pp. 55-67
Author(s):  
G. GOWTHAM ◽  
G. SHIVA SAM KUMAR SHIVA SAM KUMAR ◽  
AASA DARA
Keyword(s):  
Static Loading ◽  
Design Procedure ◽  
Initial Model ◽  
Stress Concentrations ◽  
Fighter Aircraft ◽  
Design And Optimization ◽  
High Speeds ◽  
Cantilever Structure ◽  
Standard Design ◽  
Optimized Model

An aircraft is an advanced mechanical structure made by man which has been dominating the skies from the early 19th centuries. It has been used for transportation of cargo/ passengers from one place to another in a shorter period of time. Advances in aeronautics lead to the development of fighter aircrafts with exciting and dominating characteristics. A fighter aircraft is to be designed in such a way that it can withstand heavy loadings on the wing due to its high manoeuvrability. A fighter aircraft is designed to be marginally unstable, which makes control easier and better during manoeuvrability at high speeds, but in this state there is a heavy fluctuating load acting on the wing. The wing is connected to the fuselage using wing fuselage lug attachment bracket. Since the wing is a cantilever structure, the load acting on the wing is concentrated on the hinge (lug bracket assembly). In this paper, a lug bracket is designed according to the standard design procedure and is validated using Finite Element Methods to ensure the static loading capability and stress concentrations in lug bracket. The validated model has been optimized using Altair Optistruct. The optimized model has been validated under static loading condition for the stress concentration and displacement and is compared with initial model in order to study and understand its behaviour under various conditions.

Composite Materials Manufacturing Processes

2011 ◽  
Vol 110-116 ◽  
pp. 1361-1367 ◽  
Author(s):  
Mohammad Reza Khosravani
Keyword(s):  
Composite Materials ◽  
High Performance ◽  
Fiber Composite ◽  
High Strength ◽  
Commercial Aircraft ◽  
Carbon Fiber Composite ◽  
Advanced Composites ◽  
Space Reduction ◽  
High Performance Resin ◽  
Vehicle Components

— Using Composite materials are growing more and more today and we have to use them in possible situation. One of the Composite materials applications is on the Airplane and aero space. Reduction of Airplane weight and more adaptability with nature are examples of benefit of using composite materials in aerospace industries. In this article process of manufacturing of composite materials and specially carbon fiber composite are explained. Advance composite materials are common today and are characterized by the use of expensive, high-performance resin systems and high-strength, high-stiffness fiber reinforcement. The aerospace industry, including military and commercial aircraft of all types, is the major customer for advanced composites. Product range now includes materials for low pressure and low temperature. Some using composite materials in aero space are as follow: Satellite Components, Thin Walled Tubing for Aircraft and Satellites, launch vehicle components and honeycomb structures.

scholarly journals Bending Performance and Reinforcement of Rocker Panel Components with Unidirectional Carbon Fiber Composite

Materials ◽  
2019 ◽  
Vol 12 (19) ◽  
pp. 3164 ◽  
Author(s):  
Huili Yu ◽  
Hui Zhao ◽  
Fangyuan Shi
Keyword(s):  
Composite Material ◽  
Carbon Fiber ◽  
Fiber Composite ◽  
Fiber Material ◽  
High Strength ◽  
Carbon Fiber Composite ◽  
Bending Performance ◽  
Fiber Composite Material ◽  
Crash Safety ◽  
Carbon Fiber Material

Unidirectional carbon fiber composite material is one of the most common types of composites employed in vehicles, and its bending performance plays an important role in crash safety, especially in side pole impact. This study aimed to redesign one of the most important components of the side structure of a vehicle, the rocker panel, with unidirectional carbon fiber composite material. Our results show that it is not easy to acquire the same bending performance as that of a steel rocker panel by merely replacing it with carbon fiber material and increasing the wall thickness. Therefore, reinforcements were employed to improve the bending performance of the carbon fiber rocker panel, and a polypropylene reinforcement method achieved a weight reduction of 40.7% compared with high-strength steel.

Fatigue life of a carbon fiber composite T-joint under a standard fighter aircraft spectrum load sequence

2015 ◽  
Vol 127 ◽  
pp. 260-266 ◽  
Author(s):  
M.M. Thawre ◽  
K.N. Pandey ◽  
A. Dubey ◽  
K.K. Verma ◽  
D.R. Peshwe ◽  
...  
Keyword(s):  
Fatigue Life ◽  
Carbon Fiber ◽  
Fiber Composite ◽  
Carbon Fiber Composite ◽  
Fighter Aircraft ◽  
Load Sequence

Design of Novel Solution of Flexible Pipe for Offshore Oil Offloading Transfer

2014 ◽  
Author(s):  
A. T. Do ◽  
S. Legeay ◽  
D. Charliac ◽  
J. M. Pere ◽  
J. P. Roques ◽  
...  
Keyword(s):  
Carbon Fiber ◽  
Fiber Composite ◽  
Large Diameter ◽  
High Strength ◽  
Internal Diameter ◽  
Flexible Pipe ◽  
Carbon Fiber Composite ◽  
Composite Armor ◽  
Offshore Oil ◽  
First Time

Spread moored FPSO (Floating Production and Storage Offloading) vessels are generally used for the large West African oil fields. The oil is transferred from the FPSO to shuttle tankers via an Oil Loading Terminal (OLT). 2 to 3 large diameter flexible lines are connecting the FPSO to the OLT. The final connection between the OLT and the shuttle tanker is made by floating hoses. The single length of each flexible pipe can be typically 2,300 meters or higher, and the internal diameter is generally very large in the order of 15_23″ to minimize the pressure drop and the offloading time. Conventional flexible pipe is the most suitable solution for this application. However, its long length and large diameter require a large number of buoyancy modules which are necessary to support the substantial weight generated by the steel armor wires. An alternative to steel is Carbon Fiber Composite (CFC). This material is not only twice as strong and five times lighter than a high strength steel but it is also characterized by its exceptional performance in fatigue. As the weight of the composite armor flexible pipe is significantly reduced, the use of buoyancy is no longer necessary. The pipe can also be manufactured in a single length without intermediate connection. A qualification program based on a 19″ internal diameter prototype has been launched. This is the first time that a large internal prototype with Carbon Fiber Composite Armor (CFA) and end-fittings have been designed and manufactured. The main goals are to confirm the suitability of the CFA flexible pipe for oil offloading application in accordance with the design tools. The mechanical behavior responses of the CFA are monitored by strain gages when the flexible pipe is in straight and curved positions under internal pressure and bending cycles. The paper will present the main mechanical properties and the overall performance of the flexible pipe designed and tested. The economic viability will be demonstrated by showing how the CFC material cost is positively offset by the removal of the buoyancy modules and a faster offshore installation.

A Review on Acoustic Emission Characterization of Failure Modes of Carbon Fiber Reinforced Composites

2018 ◽  
Vol 1148 ◽  
pp. 43-47 ◽  
Author(s):  
Vemu Vara Prasad ◽  
Javisseti Nageswara Rao
Keyword(s):  
Carbon Fiber ◽  
Failure Modes ◽  
Fiber Composite ◽  
Matrix Material ◽  
Acoustic Emissions ◽  
High Strength ◽  
Fiber Reinforced ◽  
Composite Sheet ◽  
Carbon Fiber Composite ◽  
Carbon Fiber Reinforced

Among various composites available for use, carbon fiber reinforced composite is unique in its Nature. Carbon fiber is an extremely strong thin fiber made by pyrolyzing synthetic fibers, such as rayon, until charred. High Strength Composites are made from this fiber by using appropriate matrix material mostly Epoxy resins are used. High Strength, stiffness, light weight and high thermal conductivity are the main advantages over the other composites. Making products with one single composite sheet is not possible always. Some of the intricate or complex shape making is required for joining of two composite sheet. The composites joining can be done in three ways mainly Adhesive, Riveting and Hybrid. Based on the Review among all these joints adhesive joining gives better economic solution in joining. Experimental results point to significant influence of fibre on mechanical properties of sample. The tensile test of the acoustic signal emission (AE) to identify the current state of material integrity in real time. Acoustic system signal correlated to damage events. The carbon fiber composite characteristic failure mechanisms are initiated on the microscale and result in a spontaneous release of elastic energy in terms of mechanical stress waves, the so-called acoustic emissions.

The Influence of Eccentricity on Thrust Force of Helical Milling in Carbon Fiber Composite Holemaking

2013 ◽  
Vol 328 ◽  
pp. 995-999
Author(s):  
Zhi Hua Sha ◽  
Yi Wang ◽  
Sheng Fang Zhang
Keyword(s):  
Composite Material ◽  
Carbon Fiber ◽  
Thrust Force ◽  
Fiber Composite ◽  
High Strength ◽  
Helical Milling ◽  
Carbon Fiber Composite ◽  
Fiber Composite Material ◽  
Tool Motion

Carbon fiber composite is widely used in aerospace and aircraft industries because of their remarkable advantages such as lightweight and high strength. As an effective holemaking technology, helical milling is widely used in machining carbon fiber composite material recently. In this paper, the mathematics modeling of tool motion in helical milling is studied and simulated; the effect of eccentricity on helical milling is analyzed and tested by experiment. From the analysis and experiment, a conclusion is drawn that: using a smaller diameter tool and larger eccentricity cause a decrease in thrust force and an improvement in delamination defects.

Isogeometric Shape Optimization for Compliant Mechanisms With Prescribed Load Paths

2014 ◽  
Author(s):  
Giuseppe Radaelli ◽  
Just L. Herder
Keyword(s):  
Shape Optimization ◽  
Degrees Of Freedom ◽  
Compliant Mechanisms ◽  
Fiber Composite ◽  
Optimization Procedure ◽  
Linear Analysis ◽  
Carbon Fiber Composite ◽  
Shape Accuracy ◽  
Initial Shape ◽  
Load Paths

This paper presents a method for the design of compliant mechanisms with large deflections and prescribed load paths. While the approach is general, this paper treats the shape optimization for two dimensional beams. Due to the geometric non-linearity of the problem the non-linear analysis is nested into the optimization procedure. This requires accurate and efficient analysis of the structural problem. The analysis of the beam is based on the Isogeometric Analysis formulation, an alternative for conventional FEA especially appreciated for its shape-accuracy and efficiency. The method is applied to the synthesis of a balancer for a pendulum, which involves a two step load case: first a prestressing phase and subsequently a motion phase under the influence of gravity. To this end, a prestressed compliant beam was optimized with respect to its initial shape and the preload conditions. The rotationless character of the degrees of freedom of the Isogeometric beam requested the formulation of specific boundary conditions in order to apply rotations on the beam. The results of the shape optimization have been validated with a prototype out of carbon fiber composite material, which has been successfully tested. The experimental results are in agreement with the simulation results, with an error of 3%.

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