This would remove the drag caused by the vertical tail and also decrease the weight of the aircraft. According to Schiltgen and Freeman [18] this could be achieved in two ways. First, by either designing fault-
Although research has been carried out in the field of in-flight thrust measurement [19], this is not currently considered to be a practical option [18]. As a result, in-flight thrust is usually deduced indirectly based on the engine operating point, whilst aircraft drag is determined based...
the example thrust reversers disclosed herein are structurally compatible with turbofan engines having relatively high bypass ratios (such as those implementing variable area nozzles) and produce efficient reverse thrust to decelerate an aircraft. However, before turning to the detailed aspects of the dis...
the example thrust reversers disclosed herein are structurally compatible with turbofan engines having relatively high bypass ratios (such as those implementing variable area nozzles) and produce efficient reverse thrust to decelerate an aircraft. However, before turning to the detailed aspects of the dis...
The size and mass of the EMA are comparatively small due to the limit of volume and weight in aircraft. In order to meet the requirements of dynamic response, the EMA should have faster tracking speed and better tracking precision than one in general industry. The EMA system in aircrafts is...
Especially for aircraft with flat fuselages, as it is often the case with unmanned aerial vehicles, this type of fluidic thrust vectoring offers straightforward integrability compared to mechanical thrust vectoring. The question of how far the results of the parametric study of the two-dimensional ...
There is a demand for a roller thrust bearing reduced in size to save energy and space and have a reduce weight (a reduced friction loss). Accordingly, the bearing in use encounters an increasingly severe condition in terms of load capacity. As aforementioned, in a roller thrust bearing a ...
Especially for aircraft with flat fuselages, as it is often the case with unmanned aerial vehicles, this type of fluidic thrust vectoring offers straightforward inte- grability compared to mechanical thrust vectoring. The question of how far the results of the parametric study of the two-...
A design space exploration is then performed on the setup to investigate how the fan stage attributes influence the trade-off between engine weight and thrust specific fuel consumption in a representative aerodynamic design point. 2. Methodology The main objective of this paper is to demonstrate an...
A design space exploration is then performed on the setup to investigate how the fan stage attributes influence the trade-off between engine weight and thrust specific fuel consumption in a representative aerodynamic design point. 2. Methodology The main objective of this paper is to demonstrate an...