Weight Optimization of Honeycomb Structures
- Paper number
IAC-05-C2.3.07
- Author
Dr. Volodymyr Slyvyns’kyy, Research Institute of Engineering Technique, Ukraine
- Coauthor
Ms. Nonna Slyvynska, Ukraine
- Coauthor
Dr. Alexander Gajdachuk, Ukraine
- Coauthor
Dr. Vitalij Gajdachuk, Ukraine
- Year
2005
- Abstract
Recently, sandwich structures with honeycomb fillers (HF), involving polymeric composite materials both in bearing skins and in honeycomb filler, are used on a broader scale in the development of space vehicles and equipment worldwide. This type of structures allows achieving the highest indices of specific strength and stiffness at minimal weight, which is a decisive parameter of their efficiency. The report includes the concept proposed by authors, as to developing weight-optimized honeycomb structures (HS) for space applications, based on the integrated implementation of the principles below: - elimination of structure zones, where incomplete utilization of material strength can occur, by using super-thin prepregs featuring thickness on the order of diameter of reinforcing monofilament obtained through special technology of carbon yarn cuts’ flattening-out; - formation of bearing skin structure maximally approaching to fluxes of forces from operational impacts; - synthesis of honeycomb filler cells, which geometrical parameters provide for achieving optimal values of the honeycomb structure shear stiffness in specific directions; - usage of intaglio method for adhesive layers’ application under honeycomb filler manufacturing, thus ensuring maximum accuracy and minimum thickness of adhesive film; - implementation of technology which minimizes adhesive consumption under its application onto honeycomb filler ends, when assembling honeycomb structures; - synthesis of honeycomb structure force diagrams providing for efficient reaction of structural elements to operating loads; - taking into consideration restrictions related to probabilistic-statistic parameters of the patterns of typical technological irregularities arising at the main stages of HS formation, when determining the target function of honeycomb structure weight minimization. Implementation of the above principles in the process of honeycomb structures’ development and manufacturing allowed reducing their weight considerably, as compared with the present analogs. Results of optimal designing of solar panels in satellites and head fairings of launch vehicles, featuring honeycomb structure with coal-plastic bearing skins, are discussed in the report as well.
- Abstract document
- Manuscript document
IAC-05-C2.3.07.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.