The load-bearing antenna approach for state-of-the-art aero-vehicle structure has been made for military aircraft in recent studies. This study presents the structural design and development of multiband aero-vehicle smart skin antenna which has been developed as a simplified structured load-bearing antenna panel compared with recent studies for aircraft. A multifunctional concept of aircraft structure combines structural and electrical functions to single structural component. The structural function of multiband aero-vehicle smart skin antenna is load-bearing member of aircraft, and its electrical function is antenna for communication and navigation of aircraft. The radar cross section and drag reduction could be achieved by using sandwich structure and composite material. Through sequential design and development process, multiband aero-vehicle smart skin antenna successfully demonstrated the design, fabrication, and structural integrity of a load-bearing multifunction antenna component subjected to flight load conditions. This study concentrated on the computational analysis using finite element to validate the structural design of multiband aero-vehicle smart skin antenna structure. In addition, structural test results were briefly introduced to compare with the analysis results. The prototype of multiband aero-vehicle smart skin antenna was fabricated and tested for the verification of each analysis within the desirable tolerance.

In this study, the natural frequencies and mode shape of an external mounting pod were verified using the modal analysis and modal testing technique for a pod mounted on an aircraft. The procedure associated with the FE model building of an external mounted pod to predict the dynamic behavior of aircraft structures is described. The simplified FE model reflecting the results of the modal testing of a pod is built through the optimization and will be applied to the structural dynamic model of an aircraft which is used to verified the stability of vibration and flutter of an aircraft.

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This paper presents the effectiveness of the thermo-mechanical design of a high-speed digital receiver unit (HSDRU) developed for spaceborne synthetic aperture radar applications. The main features of HSDRU’s thermo-mechanical design include the thermal management of high-heat dissipation units by adopting heat sinks with the additional function of structural stiffeners and securing the heat rejection path to the upper side of electronics that interfaces the foil radiator for the on-orbit passive thermal control of electronics exposed to deep space environments. The thermal design, which adopts a thermal gap pad, is closely related to the solder joint fatigue life in a launch vibration environment, owing to its initial compressive static load between the heat sink and heat dissipation units that enhances the heat transfer capability. The effectiveness of the design was validated via the qualification level of launch environment tests.

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