At the most fundamental level, main rotor loading noise is caused by the harmonically-varying aerodynamic loads (acoustic pressures) exerted by the rotating blades on the air. Rotorcraft main rotor noise is therefore, in principle, a function of rotor control inputs, and thus the forces and moments required to achieve steady, or “trim”, flight equilibrium. In certain flight conditions, the ensu...

This paper conducts an investigation towards main aircraft cabin parameters. The aim is two-fold: First, a handbook method is used to preliminary design the aircraft cabin. Second, an objective function representing the “drag in the responsibility of the cabin” is created and optimized using both an analytical approach and a stochastic approach. Several methods for estimating wetted area and ma...

--------------------------------------------------------Abstract------------------------------------------------------------Structural loads are critical for aircraft design, especially joining members of the system. Wings, they are joining with fuselage through a structural member called fairings, these fairings plays major role in aerodynamic and structural factors of the wing and fuselage sy...

In this paper, topology optimisation is applied to the design of the rear fuselage of an unmanned aerial vehicle (UAV). A comparison is drawn between the performance of a design created through evolutionary structural optimisation (ESO) and a baseline design modelled on a manually designed and successfully flow fuselage geometry, for different wing shapes. The loading for each wing shape is det...

A methodology to estimate the cost implications of design decisions by integrating cost as a design parameter at an early design stage is presented. The model is developed on a hierarchical basis, the manufacturing cost of aircraft fuselage panels being analysed in this paper. The manufacturing cost modelling is original and relies on a genetic-causal method where the drivers of each element of...

An acoustics parametric analysis of the effect of fuselage drag and pitching moment on the Blade-Vortex Interaction (BVI) noise radiated by a medium lift helicopter (S-70/UH-60) in a descending flight condition was conducted. The comprehensive analysis CAMRAD II was used for the calculation of vehicle trim, wake geometry and integrated air loads on the blade. The acoustics prediction code PSU-W...

Previous studies have indicated more birds collide with communication towers equipped with red warning lights than with towers equipped with lights of shorter wavelengths. We used the U.S. Federal Aviation Administration’s National Wildlife Strike Database to determine if a similar relationship exists for turbine-powered jet aircraft with 2 underwingor fuselage-mounted engines and bird strikes....

SMART, Solid Modeling Aerospace Research Tool, isthe Vehicle AnalysisBranch of NASA Langley Research Center's computer-aided design tool used in aerospace vehicledesign. Modeling of structuralcomponents using SMART includes the representationof the transverseor cross-wiseelements of a vehicle'sfuselage,ringframes and bulkheads. Ringframes are placed along a vehicle'sfuselage to provide structur...

Aircraft is a complex engineering structure. The safety of the structure and weight are two important aspects to be kept in mind while designing aircraft It an uphill task for structural designer bring out safest with minimum weight. current project deals stress analysis fuselage-stiffened panel without large cutout emergency exit door. Cabin pressurization load case, which one critical cases u...