.......................................................................................................................................... 4 Introduction .................................................................................................................................... 5 Prior Projects and Research ...................................................................................

This paper deals with the study and comparison of passive and active landing gear system of  the aircraft and dynamic responses due to runway irregularities while the aircraft is taxying. The dynamic load and vibration caused by the unevenness of runway will result in airframe fatigue, discomfort of passengers and the reduction of the pilot’s ability to control the aircraft. One of the objectiv...

This dissertation presents a control law for helicopters to reduce vibration and to increase damping using individual blade control. control synthesis is used to develop a robust controller usable in different operating conditions with different helicopter flight speeds. The control design is applied in simulation to the four-blade BO 105 helicopter rotor, which is equipped with an individual b...

NASA has been a leader in development of composite materials for aircraft applications during the past 25 years. In the early 1980’s NASA and others conducted research to improve damage tolerance of composite structures through the use of toughened resins but these resins were not costeffective. The aircraft industry wanted affordable, robust structures that could withstand the rigors of flight...

Medium helicopter armour concept is discussed. Basic analysis of armour configuration on helicopter fuselage is described. Important zones and requirements for their protection are analyzed as well. Aerodynamic characteristics of medium helicopter are obtained using numerical simulation and wind tunnel tests.

An experimental study was performed to design and analyze a "pusher" propeller for use by a small, expendable, autonomous unmanned aerial vehicle (UAV) whose mission was to descend from 30,000 feet to sea level at an approximately constant descent rate over a 3-hour mission duration. The entire propeller design process, from airfoil selection to final part generation in the computer-aided draft...