PHASE III DUAL USE APPLICATIONS: These metamaterials will enable the development of a laminate that can be added to any composite material to provide a fast, low cost, high resolution non-destructive test capability using a compact hand-held sensor. It will find military application via industrial fabrication capability applied to most military vehicle and aircraft programs of record. Adoption by industry will be stimulated by the advantages for commercial vehicles, aircraft, and composite structures. This technology will significantly reduce operating cost, life-cycle costs, and accident costs.
PHASE III DUAL USE APPLICATIONS: Chalcogenides such as these can be used in systems which use thermal systems. Potential commercial applications include thermal security cameras for use in Homeland Security applications (perimeter security at airports, coastal ports, nuclear power installations), UAV sensors, as well as satellite sensors. The possibility to incorporate these structures into current sensors could also be explored, for the potential use in both ground vehicles and aircrafts. Additionally, selenide-based chalcogenide glasses are already widely employed in the athermal imaging systems, especially in the low-cost IR system of auto navigation. [Lin] Finally, such optics may be used to increase the thermal stability of SWIR cameras.
Aircraft Structures Dj Perry Pdf Download
A review of morphing concepts with a strong focus on morphing skins is presented. Morphing technology on aircraft has found increased interest over the last decade because it is likely to enhance performance and efficiency over a wider range of flight conditions. For example, a radical change in configuration, i.e. wing geometry in flight may improve overall flight performance when cruise and dash are important considerations. Although many morphing aircraft concepts have been elaborated only a few deal with the problems relating to a smooth and continuous cover that simultaneously deforms and carries loads. It is found that anisotropic and variable stiffness structures offer potential for shape change and small area increase on aircraft wings. Concepts herein focus on those structures where primary loads are transmitted in the spanwise direction and a morphing function is achieved via chordwise flexibility. To meet desirable shape changes, stiffnesses can either be tailored or actively controlled to guarantee flexibility in the chordwise (or spanwise) direction with tailored actuation forces. Hence, corrugated structures, segmented structures, reinforced elastomers or flexible matrix composite tubes embedded in a low modulus membrane are all possible structures for morphing skins. For large wing area changes a particularly attractive solution could adopt deployable structures as no internal stresses are generated when their surface area is increased. 2ff7e9595c
Comments