Differential thrust can be used for directional control on distributed electric propulsion aircraft. This paper presents an assessment of flight dynamics and control under engine inoperative conditions at minimum control speed for a typical distributed propulsion aircraft employing differential thrust. A metho...
on mechanical deflection components. According to Alcorn et al. [2], the replacement of conventional aerodynamic control surfaces brings enormous advantages, which include the improvement of low-observability (LO) as well as the reduction of aircraft mass and zero-lift dragCW0. This can result in...
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...
weightreductionpurposesthisaircrafthasonlytwothrustreversers.They areinstalledonthetwoinboardengines. 8.1.2ReverserOperation Athrustreversersystemisdesignedfortheuseongroundonly.Thesys- temisequippedwithsafetyfeaturespreventingthedeployingoftherever- serduringflight.Duringlandingthethrustreverserisdeployedshortlyaf- ter...
The development of rockets has led to larger values of thrust-to-weight and length-to-diameter ratios as required for longer range flights. The drag force is proportional to the square of the rocket diameter, and therefore the preference is to vary the length as opposed to the diameter for ...
The development of rockets has led to larger values of thrust-to-weight and length-to-diameter ratios as required for longer range flights. The drag force is proportional to the square of the rocket diameter, and therefore the preference is to vary the length as opposed to the diameter for ...
compared to the control region (for 10 m/s <𝑣𝑠vs< 35 m/s), where the curves are much steeper. There is a marginal increase in slope in the saturation region (𝑣𝑠vs> 35 m/s), where effective thrust vectoring is not feasible. Therefore, from an aircraft control perspective, ...
In recent years, the demand for Urban Air Mobility (UAM) and Micro Aerial Vehicles (MAVs) has driven the emergence of new aircraft designs, with the Staggered Rotor System being widely applied in these vertical take-off and landing aircraft. Due to the c
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...
During the cruise, this engine will be underutilized as the drag to be countered is only a small fraction of the weight. Furthermore, the larger engine size could also increase the profile drag of the aircraft, whereas the hybrid rocket based VTOL system is designed to produce high thrust ...