The traditional vertical axis wind turbine will produce a part of mechanical loss because of the transmission system between the wind wheel and generator, resulting the reduction of the wind energy utilization rate of the wind turbine. This paper proposes a new design method for off-grid small vertical axis wind turbine. The wind wheel is directly connected with the outer rotor of the generator that directly driven by the wind wheel needn't other transmission device, thereby effectively reducing the mechanical loss and the manufacturing cost of the wind generator, improving the utilization rate of the wind energy.

This article aims to provide an interactive in-house tool to quickly asses the stress in

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For aerospace vehicles, such as rockets and satellites that are subjected to high mechanical and thermal loading, it is necessary to better understand how the structure is influenced by these loads. Because reducing the mass of the structure while maintaining strength is a very important requirement, field-tested components will be subject to different SFs (safety factors) than those that are only subjected to FEA (Finite Element Analysis). Also to further reduce the magnitude of the load factors in the MOS (Margin of Safety) calculation, mechanical loads are considered to have a different safety factor than the thermal loads. This paper proposes a solution, a tool developed to calculate MOS for structural parts for different safety factors on mechanical and thermal loads, based on data obtained from FEA. The tool takes as input the results from the NASTRAN result files and creates one excel file with MOS for each component requested by the user and different types of summary.

Sinusoidal vibrations represent an ideal case. Technically, it is quite hard to generate pure sinusoidal vibrations without containing other spectral components, called harmonics. Sinusoidal vibrations can appear on propeller, propulsion and turbofan aircraft as well as on helicopters and aerospace structures. They can occur during different phases of flight (take-off, ascent, cruise, landing, etc.). The aim of this article is to present how a structure can be validated by using the mathematical formulas or a FEM software such as PATRAN-NASTRAN (and the equations behind it).As an application, an aerospace structure such as thruster brackets will be analyzed. A sinusoidal signal of 1g was applied on the attachment points and the response was read from the center of gravity of the thrusters.