There are many established techniques such as Genetic Algorithm (GA), Simulated Annealing (SA),Taboo Search, (TS), Ant Colony Optimization (ACO).In this study GA and SA techniques are used for optimization purpose. Most of the engineering applications require high strength and corrosion resistant materials for long term reliability and performance. By cladding these properties can be achieved with minimum cost. In order to achieve minimum cost the process parameters has to be optimized. This paper highlights an experimental study to optimize various input process parameters (welding current, welding speed, gun angle, contact tip to work distance and pinch) to get optimum dilution in stainless steel cladding of low carbon structural steel plates using Gas Metal Arc Welding (GMAW). Experiments were conducted based on central composite rotatable design with full replication technique and mathematical models were developed using multiple regression method. The developed models have been checked for adequacy and significance. In this study Simulated Annealing (SA) and Genetic Algorithm (GA) techniques are integrated to estimate optimal process parameters that to a minimum parameters that lead to optimum value of Dilution.

The main goal of the proposed paper is the numerical investigation of Wings with and without winglet designs. This investigation shows the various performance and parameters for the wings when designed with a winglet and without a winglet and thus comparing the parameters for both the designs. The discussions were focused on the aerodynamics characteristics which include drag coefficient CD, lift coefficient CL, and lift-to-drag ratio L/D. In this investigation two Different wings are used: An Elliptical wing and a Short wing. The airfoil used in this investigation is NACA 2412 with which both the wings are designed. The Geometry of the models is carried out in the CATIA V5 R19 Software and is designed in Part and Wireframe and Surface Design. The airfoils of Different Chord length are designed with different Stations using the geometry given in the DESIGNFOIL Software. The winglet is then designed for both the wings. The investigation aims to produce better aerodynamic performance with the implementation of the winglet for both wing designs. One of the objectives of this work is reduce the induced drag formed on wing during the fight operation, thus improving the efficiency of the aircraft. The analysis part is done by using the ANSYS Software, flow parameters (like the lift and drag) are measured for different design configurations and are compared with the plane wing and the wing designed with winglet.

This document gives Information About the Reaction Control Systems used for space shuttle for Maneuvering, Steering and Attitude control of the Spacecraft during its flight.

Fatigue is progressive failure mechanism and material degradation initiates with the first cycle. The degradation/damage accumulation progresses until a finite crack is nucleated, then the crack propagates until the failure process culminates in a complete failure of the structures. The total life from first cycle to the complete failure can be divided into three stages: Initial life interval, Life interval, Final Life interval. The fatigue damage is mainly based on two designs: FAIL-SAFE and SAFE-LIFE. The objective is to design a Fail-Safe Structural component. In this project we have designed a Wing-Bracket interaction which was not yet designed by any of the industry. And we have estimated the fatigue life of our Wing-Bracket attachment model. Here we compared the fatigue life of our model with three materials such as Maraging Steel, Titanium and Structural A36 steel. Among this three we have proved that Maraging steel gives more fatigue life compared to other two materials. For estimating the fatigue life we have made some hand calculations. Finally we have represented the fatigue life with the help of Goodman Curve. The Structural Component is designed and analysed using CATIA and ANSYS Softwares. In analysis the maximum stress at which the component undergoes degradation/damage is calculated for different End Conditions (loadings and stresses), which determines the fatigue life of the component.