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The missile guidance law utilizing variable structure control is proposed. The acceleration command input is determined considering the target acceleration as uncertainty. The target and the missile are assumed to be point masses moving in a twodimensional plane. According to the property of missile acceleration, the proposed guidance law can be classified into the IPN type and the RTPN type. It is also shown that the conventional proportional guidance laws can be derived from the proposed guidance law. To compensate for the effects of the uncertainty in the target acceleration, the perturbed guidance command is introduced. Numerical simulations show that the proposed guidance law yields better performance compared to the conventional proportional guidance laws.

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This paper presents a low pressure hot embossing method for transferring patterns of vertically aligned carbon nanotubes into thermoplastic substrates. The procedure utilizes the synthesis of carbon nanotubes in discrete patterns on silicon substrates through the vapor liquid solid growth mechanism. The nanotube pattern and silicon stamp is placed on top of a polycarbonate film and locally heated above the glass transition temperature using microwave processing. The weight of the silicon substrate presses the nanotubes into the polycarbonate, resulting in the complete transfer of vertically aligned patterns. The technique is a rapid processing method, which could be used to integrate aligned nanomaterials with MEMS and flexible electronics that are fabricated on a wide range of thermoplastic polymer materials.

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