Implementation of "MSG-3" for Crack Growth Analysis of Aircraft SSI Components

علیرضا نکویی

Volume 10, Issue 1 , March 2013

Abstract
  The main goal of this article is to implement the MSG-3 process in structure field for an SSI component of b747 aircraft. This process is expected toincrease the ease of aircraft maintenance and its safety level. MSG-3 logic took a top-down or consequence of failure approachmeaning that MSG-3 reduces ...  Read More

Rotor Sizing of Helicopters Using Statistical Approach

فرید شاهمیری

Volume 10, Issue 1 , March 2013

Abstract
  This paper is concerned with the statistical model development issues, necessary for rapid estimation of the rotor sizing for single main rotor helicopters at the preliminary design stage. However, Central Composite Design (CCD) method, simulation-based data collection, linear regression analysis, mathematical ...  Read More

Extracting Dynamics Matrix of Alignment Process for a Gimbaled Inertial Navigation System Using Heuristic Dynamic Programming Method

امیرعلی نیکخواه

Volume 10, Issue 1 , March 2013

Abstract
  In this paper, with the aim of estimating internal dynamics matrix of a gimbaled Inertial Navigation system (as a discrete Linear system), the discretetime Hamilton-Jacobi-Bellman (HJB) equation for optimal control has been extracted. Heuristic Dynamic Programming algorithm (HDP) for solving equation ...  Read More

Simulation of Pitching and Heaving Airfoil with Oscillation of Flow Boundary Condition

M.H Djavareshkian; A.M. Faghihi

Volume 10, Issue 1 , March 2013

Abstract
  A pressure based implicit procedure to solve the Euler and Navier-Stokes equation is developed to predict transonic viscous and inviscid flows around the pitching and heaving airfoils with a high reslution scheme. In this process, nonorthogonal and non moving mesh with collocated finite volume formulation ...  Read More

A Three Stage Terminal Fuzzy Guidance Law for Reentry Vehicles

J. Karimi; M. Shadoud

Volume 10, Issue 1 , March 2013

Abstract
  An advanced guidance law is developed for reentry phase of a reentry vehicle. It can achieve small miss distance and desired impact attitude angle, simultanceously. To meet this requirment a guidance law based on the fuzzy logic approach is developed. It is partitioned into three stages. This guidance ...  Read More

Nonlinear Dynamic Modeling and Hysteresis Analysis of Aerospace Hydro - dynamical Control Valves

علی جعفرقلی; حسن کریمی مزرعه شاهی

Volume 10, Issue 1 , March 2013

Abstract
  A new procedure for deriving nonlinear mathematical modeling for a specific class of aerospace hydro - mechanical control valves is presented. The effects of friction on the dynamic behavior of these types of valves along with the experimental verifictions are also given. The modeling approach is based ...  Read More