In the present paper we describe the CAGD part of an effort that aimed at the unification of the whole geometric preprocessing that preceded the wind tunnel readings with a realistic air-plane wing model in a recent research project. This preprocessing includes the automated generation of the CAD models which were used for the manufacturing of the multi-parted wing-fuselage configuration and th...

By hybrid aircraft, we mean a UAV that can vertically take-off, land and hover like a helicopter, and meanwhile can be converted to a fixed wing airplane to achieve high forward speed and long endurance than normal helicopters. This paper presents our recent work on control of a novel small scale hybrid aircraft. The proposed aircraft should follow a specific trend of trajectory to be able to c...

The phenomenon of overbanking tendency for a rigid-body, fixed-wing aircraft is investigated. Overbanking tendency is defined as a spontaneous, unbalanced rolling moment that keeps increasing an airplane’s bank angle in steep turns and must be arrested by opposite aileron action. As stated by the Federal Aviation Administration, the overbanking tendency may lead to a loss of control, especially...

The accumulation of ice on an airplane in flight is one of the leading contributing factors to general aviation accidents. To date, only relatively sophisticated methods based on detailed empirical data and flight data exist for its analysis. This paper develops amethodology and simulation tool for preliminary safety andperformance evaluations of airplane dynamic response and climb performance ...

Fixed-wing unmanned aerial vehicles (UAVs) with the ability to hover have significant potential for applications in urban or other constrained environments where the combination of fast speed, endurance, and stable hovering flight can provide strategic advantages. This paper discusses the use of dynamic inversion with neural network adaptation to provide an adaptive controller capable of transi...

1310402-9595-IJET-IJENS © April 2013 IJENS I J E N S  Abstract— The purpose of this work is to present a methodology to ensure the metrological confidence during measurement of aerospace parts by ultrasonic, focusing the thickness measurement of an airplane wing skin. This methodology involves from the criteria used to perform the selection of a proper measurement system (ultrasonic) to the es...

INTRODUCTION The Federal Aviation Administration's Integrated Noise Model (INM) is one of the primary tools for land use planning around airports [1]. The INM currently calculates airplane noise lateral attenuation using the methods contained in the Society of Automotive Engineer's Aerospace Information Report No. 1751 (SAE AIR 1751) [2]. Researchers have noted that improved lateral attenuation...

We describe an algorithm for automated generation of multi-parted airplane wings from a cross-section given by a point cloud and the top view of the wing. The relative thickness of the wing (thickness/chord) can be varied from section to section. A rounded tip with two design parameters and GC1-continuity at the crossing to the wing is automatically computed. Constrained approximation and fairi...