This paper focuses on the research and development of the “Multi-functional Composite Embedded Smart-Skin Antenna (MECSSA) Structure” with load-bearing, shape maintaining and communication capabilities. MECSSA structure consists of top and bottom composite thin facesheet, honeycomb core, 4 by 8 micro-strip antenna arrays located among honeycomb core and some adhesive. Simulation and experiment methods were used to study the performance of MECSSA structure. Through the study we found that adhesive is the significant factor of affecting the electrical performance of MECSSA structure, especially for radio frequency (RF) and it must take into account in the research. There may be two ways to avoid the influence of adhesive: compensation and separation. Three point bending test indicated that the strength of MECSSA structure satisfies design requirements.

This paper introduces the research work on the development of a Smart Skin Antenna Structure (SSAS) for Global Navigation Satellite System (GNSS) by embedding a navigation antenna with working frequency from 1.2GHz to 1.6GHz into a composite sandwich structure. The structure possesses the load-bearing, shape maintaining and navigation capabilities at the same time. Numerical models have been generated to design and evaluate the EM property of this multifunctional structure. Specimens have been manufactured and tested. The test data show relatively good correlation to the numerical results.

The equivalent thermal conductivity of superalloy honeycomb core structures have been studied by experimental method. Test results show that the decrease in honeycomb core height and the increase in honeycomb core diameter would lead to a lower equivalent thermal conductivity for superalloy honeycomb cores. Filling adiabatic materials such as ZrO2 fibers and SiO2 aerogels into core cells would significantly reduce the equivalent thermal conductivity of honeycomb cores with a minor penalty in structure weight.

In accordance to ASTM test standards, this paper presents experimental studies on quasi-static indentation tests on sandwich panels with carbon fiber reinforced facesheet and foam core. The indentation force vs. displacement curves were obtained. A series of tests with different indentation depth were carried out to study the damage modes and damage propagation process of foam core sandwich panels under quasistatic indentation force.

The residual compressive strength of a foam core sandwich panel after low-velocity impact was studied by using experimental and analytical methods. The test specimens were compressed uniaxially after they were subjected to a low-velocity-impact. From the observation in the test, one can conclude that the subsequent core crushing around the impact region is the major failure mode in the sandwich structure. A failure criterion named Damage Propagation Criterion was proposed to predict the residual compressive load bearing capability of the low-velocity impacted composite sandwich panel. The characteristic value used in this failure criterion can be calculated by an analytical model developed or by conducting the Sandwich Compression after Impact test.