A great necessity for the optimal designing and manufacturing of size-stable and precision structures for satellite communication systems and sensing systems has arisen for the successful implementation of the international space programs. It is known that the sandwich panel with load-bearing layers made of polymer composites based on carbon, organic or glass fibers and honeycomb filler of aluminum foil or other materials have a high size-stability. This class of structures is exposed to large overload during the launching, vibration effects and thermal cycling in the specific conditions of space. Providing of minimum weight and maximum stiffness under these conditions of the size-stable composite honeycomb structures designed for space purposes is due to a number of features and problems in their production. The main trend in designing and producing of ultra-strong and size-stable sandwich structures based on carbon filler has been shown for the product intended for use in space. Optimization of the design parameters was performed on a sample of real section of the composite solar panel with honeycomb filler. Results of the analysis of different reinforcement schemes for load-bearing layers and rational distribution of material for several load cases were presented. Analysis and assessment of technological warpage of these panels was carried out. The causes of defects generated during the manufacturing process in the form of continuous and discrete strips of thin CFRP load-bearing skins were also investigated. Complex investigation of adhesive joint's bearing capacity of composite skins with a honeycomb filler at transverse avulsion for the main technological methods of applying the glue (in the form of a continuous layer and targeted dosing to the ends of the honeycomb) was carried out by the analytical method and using finite element method. The obtained results allow predicting the fracture behavior of the compound of load-bearing layers with honeycomb core depending on the parameters and material properties of the honeycomb and the adhesive layer. Optimization of the design parameters of the solar panel's composite section with honeycomb filler have predicted its surface mass at level 0.6 kg/m.sq. if implementing of modern achievements in the field of polymer composite materials and manufacturing technologies of composite structures. It is noted that the use of CFRP as a material of filler can significantly increase the efficiency of the thermo-stable and size-stable aggregates for space technology and allows recommending specific objects that implement the obtained results.
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机译：为了成功实施国际空间计划，迫切需要为卫星通信系统和传感系统进行尺寸稳定和精密结构的最佳设计和制造。已知具有由基于碳，有机或玻璃纤维的聚合物复合材料以及铝箔或其他材料的蜂窝状填料制成的具有承载层的夹心板具有高的尺寸稳定性。此类结构在特定空间条件下的发射，振动效应和热循环过程中会承受巨大的过载。在这些条件下，为空间目的而设计的尺寸稳定的复合蜂窝结构在这些条件下提供最小的重量和最大的刚度是由于其生产中的许多特征和问题。对于用于太空的产品，已经显示出设计和生产基于碳填料的超强且尺寸稳定的三明治结构的主要趋势。设计参数的优化是在带有蜂窝状填充物的复合太阳能电池板的实际截面样本上进行的。给出了承载层不同加固方案的分析结果以及几种情况下材料的合理分布的结果。对这些面板的技术翘曲进行了分析和评估。还研究了在制造过程中以连续的和离散的CFRP承重蒙皮条形式产生缺陷的原因。通过分析，对蜂窝状填料在横向撕开时复合表皮的胶接点承载力进行了综合研究，以研究胶水（以连续层的形式并有针对性地加到蜂窝状末端）的主要技术方法。方法和使用有限元方法。所获得的结果允许根据蜂窝和粘合层的参数和材料特性来预测具有蜂窝芯的承载层的复合物的断裂行为。蜂窝状填充的太阳能电池板复合部分设计参数的优化预测其表面质量为0.6 kg / m.sq。是否实施了高分子复合材料和复合结构制造技术领域的现代成就。应当指出，使用CFRP作为填充材料可以显着提高航天技术的热稳定和尺寸稳定的骨料的效率，并可以推荐实现所获得结果的特定对象。
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