The implementation of composite materials in industries like aerospace, automotive, civil, naval, etc., are emerging continuously because of its combined unique effects. The present article deals with a numerical simulation of the natural frequency effect on the different cantilever structure for various composite materials also estimates its structural response to aerodynamic forces using Fluid-Solid Interaction (FSI) in Ansys Workbench environment. This work is intended to analyze and learn the response of various real-time structural parameters like maximum deformation, maximum stress-induced location and modal parameters like modal frequency, mode shapes on different Cantilevered structures. Structures like wind turbines, airplane wings are critical in structural behavior, which are characteristically using the wind to produce power and lift respectively. The present article deals with an estimation of natural frequencies for the prediction of working lifespan and structural parameters variation throughout the cantilever structures to multi-purpose usage. The entire comparative part of this article is executed with an acceptable simulation of the displacement and principal stress for different composite materials such as Kevlar, Glass Fiber Reinforced Plastic (GFRP) and Carbon Fiber Reinforced Plastic (CFRP) by using FSI. Composites Beams are modeled in CATIA and discretized in the Ansys ACP 16.2 tool and Modal analysis of various cross-sectional beams are reported, compared and discussed.

At present, surveillance is attracting attention in the field of UAV development. In particular, border surveillance plays a vital role in obtaining the required data around the border and for assisting in military operations. The primary function of this Hybrid UAV (VTOL and Fixed Wing) is to provide prerequisite data, captured during day/night surveillance, to the respective database. One of the primary problems that arise in border patrolling is the use of the UAV under different environmental conditions, thereby reducing its endurance firmly. In addition to the surveillance equipment, energy harvesting techniques are involved in solving the problem of endurance. The piezoelectric energy harvester and solar panels are added to harvest electrical energy in the UAV. Based on this application, the conceptual design of the Hybrid UAV, based on nature, was designed and investigated theoretically, as well as computationally. A series of analysis, which includes Computational Fluid Dynamics, Finite Element Analysis and Analytical approach, was used to determine the energy harvested from the energy harvester. This work confirms the proposed integrated engineering approach for the estimation of renewable energy, via PVEH patches, and the same approach is thus offered to researchers for subsequent applications. Additionally, a hybrid energy idea for newly developed drones was proposed in this work. This concept will be extensively used in the unmanned aircraft system sectors.

The objective of this paper is to estimate the fatigue life behaviour of Al 7075-T6 using experimental and numerical methods for the purpose of aerospace applications. In this paper, initially static properties for the specimens are determined using Universal Testing Machine (UTM) under tensile loading. The cyclic bending load is applied on the material using fatigue test and the dynamic properties are determined. Experimental and numerical studies are carried out to determine the fatigue strength and endurance limit values of aluminium alloy 7075-T6 at different types of loading. The fatigue strength and structural integrity of the aluminium alloy 7075 - T6 are investigated using S-N curve. In numerical simulation, the reference model of this paper has been modelled by CATIA and thereby it is imported into ANSYS workbench 16.2 to investigate the stress distribution and number of cycles to failure of an aluminium alloy 7075-T6 under tensile loading. The mechanical properties are evaluated using both the approaches and finally the comparative study is carried out.

Nozzles are used to produce thrust in airplanes, rockets, and even satellites. Different designs are employed for various applications. For propelling satellites in space, High Area Ratio supersonic nozzles (A.R. > 100) are used. During ground tests of these nozzles, it is found that a shock wave is formed and flow tends to separate in divergent section. A second throat ejector diffuser system (STED) is employed to simulate ambient vacuum conditions at high altitudes, in sea level, around the nozzle. This vacuum level is maintained throughout the test times and is used for smooth expansion of the gas across the nozzle without flow separation. The Shockwaves formed in the diffuser help in maintaining the desired lowpressure levels and reduce the flow velocity and increase the pressure. A High Area Ratio nozzle (A.R.= 114) and a Second Throat Diffuser are designed and modeled together. The flow analysis is carried out using CFD and the pressure, velocity and temperature variations in the nozzle and diffuser are studied. The diffuser design is then optimized, by varying different parameters of the diffuser, and analysis is carried out for each design in order to obtain full flow in the nozzle and the diffuser. The design of the diffuser must be such that the flow in the nozzle must be stable and should provide a suitable pressure recovery with the reduction in flow velocity. After the diffuser design is finalized, performance analysis of the diffuser is carried out, along with the nozzle, in order to achieve the working conditions of the diffuser.