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Analysis of the Use of Mathematical Modeling Results for the Determination of the Stress-Strain Behavior and the Resource of Space & Aviation Mechanical Details
Submission DeadlineAug. 20, 2020

Submission Guidelines: http://www.sciencepublishinggroup.com/home/submission

Lead Guest Editor
Tatiana Pribora
Aero Engines Manufacturing Department, Institute of Aviation, Aerospace University, Kharkiv, Ukraine
Guest Editor
  • Mahmoud Elkady
    Department of Manufacturing Engineering for Space Launch Vehicles, Faculty of Physics and Technology, Dnipro National University, Dnipro, Ukraine
Introduction
The most accurate determination of the stress-strain behavior of a calculated object is the basis for providing it with a reliable resource. Mathematical modeling implemented on the use of the ANSYS computational complex provides sample opportunities for solving the challenging tasks of designing aircraft gas turbine engines, details made of polymer composite materials and elastomeric materials for space applications, and nano fillers. The accuracy of the results obtained with finite-element calculation depends directly on the element mesh quality and, in particular, on the size of the finite element. The designed complex offers the use of the “submodeling” service to achieve the required accuracy of calculations when assessing the stress-strain behavior of the critical parts of the gas turbine engines, rocket motors made of composite materials with nano materials as filler. The mathematical model of the critical details like compressor impeller was initially a “heavy” model with a large number of finite elements and with complex non-linear parameters. Achieving sustainable values of stress and strain in the critical zone, while reducing the element size, is a long and impractical process. "Submodeling" service in this case is relevant. In this special issue, the methodology of determining the most realistic stress-strain behaviour of critical parts of aircraft gas turbine engines and rocket motors will be introduced, first paper namely: the use of submodeling for multiple sequential reducing the finite element mesh in the critical zone of the compressor disk until getting a stable calculation result was offered. The final result of the first issue such a calculation in the form of the total deformation value is used to determine the predicted durability from low-cycle fatigue curves using a “hard” cycle. Second paper will be numerical analysis of the vital process of the rocket body fragments made of structural elastomeric materials. The third one shall be ensuring reliable operation of rocket shock absorbers using numerical analysis (more than two parts).
Aims and Scope:
  1. Stress-strain behavior
  2. Aircraft gas turbine engines
  3. Solid-propellant rocket motors
  4. Polymer composite materials
  5. Elastomeric materials
  6. Nano fillers
  7. Critical part areas
  8. Mathematical model
  9. Submodel
  10. Resource increasing
Guidelines for Submission
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(see: http://www.sciencepublishinggroup.com/journal/guideforauthors?journalid=309).

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