Optimization of design parameters of the main composite fairing of the launch vehicle under simultaneous force and thermal loading
Authors:
- A.V. KondratievA.V. Kondratiev
- V.O. KovalenkoVKV.O. Kovalenko
- 1 January 2019
- journal article
- research article
- Published by National Academy of Sciences of Ukraine (Co. LTD Ukrinformnauka) (Publications) in Kosmìčna nauka ì tehnologìâ
- Vol. 25 (4) , 3-21
Abstract
No abstract availableKeywords
This publication has 8 references indexed in Scilit:
- Weight-based optimization of sandwich shelled composite structures with a honeycomb fillerEastern-European Journal of Enterprise Technologies, 2019
- Stabilization of physical-mechanical characteristics of honeycomb filler based on the adjustment of technological techniques for its fabricationEastern-European Journal of Enterprise Technologies, 2018
- Changes in the Thermal and Dimensional Stability of the Structure of a Polymer Composite After CarbonizationMechanics of Composite Materials, 2017
- Anisogrid composite lattice structures – Development and aerospace applicationsComposite Structures, 2012
- New Concept for Weight Optimization of Launcher Nose Firings Made of Honeycomb Structures2006
- Finite element analyses of sandwich structures: a bibliography (1980–2001)Engineering Computations, 2002
- A computational study in optimum formulations of optimization problems on laminated cylindrical shells for buckling II. Shells under external pressureComposites Science and Technology, 2000
- A computational study in optimum formulations of optimization problems on laminated cylindrical shells for buckling I. Shells under axial compressionComposites Science and Technology, 2000