Hybrid aircrafts are unique type of aircrafts that combine the hover capability of helicopters with the speed and range of airplanes. In this work, we propose a novel hybrid aircraft based on the fixed-wing airplane and quad rotor structures. A complete mathematical model of the aircraft, in helicopter, transition and airplane flight modes is presented. Finally, simulation results are presented in order to illustrate performances of the proposed controller. The proposed UAV structure configuration is similar to V-22 osprey however it is designed based on the propeller thrust instead of jet-engines In any hybrid aircraft, the transition between hover flight and cruise flight is the most difficult regime to achieve and convertible rotor aircraft are no exception to this The design has been developed as UAV which is propelled by motors which has all the abilities of flight controls equipped in a single body. Which has a specification of weight up to 4kg's Future work will consist of creating a more detailed model for lift and drag.
Moore's law states that the technical innovations are being absorbed already. The device's controllability has dramatically improved since moving from a straightforward metal oxide semiconductor field effect transistor (FET) constructed with a single control gate to one with many control gates. Here, the device-level simulation of vertically stacked GAA nanosheet FET is performed, for which the various geometrical variations are calibrated to examine the impact of these geometrical variations on the device's performance. The most prominent parameters like ION, IOFF, SS, DIBL, switching ratio, and threshold voltage values are analyzed. For the device to be considered to have better performance ION should be maximum, IOFF should be minimum. Hence, to obtain this, the thickness of the nanosheet is varied on the scale of 5 to 9 nm, and the width is varied from 10 to 50 nm. The device simulation and analysis are performed using the Visual TCAD - 3D Cogenda tool.
In this paper, the study of the aerodynamic performance of the aircraft which operates in both Hypersonic and Supersonic Flows has been carried out. The aerodynamics of the objects in these two regimes varies and is different in each. There is necessity for understanding the flow characteristics and applying it to a design which should be efficient in both the regimes. The project suggests that an adjustable spike system at the nose of the aircraft can improve the aerodynamic performance at small weight compensation.
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