Efficiently evaluate the sizing of key aerodynamic features and various control methodologies to aid in the design and flying of the Martin Jetpack. 2.2.1 Duct Reactions. Duct Thrust Figure 4 shows a cross-section of the air flow through a ducted-fan control volume with the fan represented by an actuator disc (solid line). A COMPUTATIONAL AND EXPERIMENTAL ANALYSIS OF A. The ducted fan design and performance analyses were. The equations 1, 2 and 3 are integrated over control volume.

• • Part of the book series (LNCS, volume 3398) Abstract A computational model been developed for an axisymmetric ducted fan system to identify its design parameters and their influence on the system performance. The performance of the system has been investigated as its geometrical design parameters, its fan model parameters, and the thrust requirement are changed parametrically. The fan in the system is modeled as an actuator disk, which provides jumps in stagnation enthalpy and stagnation density across it. Current results show that increasing diffuser angle of the duct improves the propulsion efficiency of the ducted fan system, while the inlet geometry has little effect on it.

Also, non-uniform fan strength distribution models have been proposed and investigated, which shows that the strength distribution of the fan increasing in the direction of the fan blade tip facilitates wake expansion and requires less power than the fan strength distribution which increases in the direction of the blade hub. The current results are to be validated in near future, when the experimental and computational results are available from parallel research works.

Ducted fan UAV (Unmanned Aerial Vehicle) has broad application prospective. To study flight dynamics and flight control problems of ducted fan UAV, this paper developed a refined aerodynamic model for the ducted fan UAV by wind tunnel test. Based on that, the flight dynamic model of ducted fan UAV was built, which showed features as being nonlinear and unstable and of strong coupling and, therefore, inspired this paper to adopt a strong adaptive control approach based on decoupling to perform attitude control on the ducted fan vehicle. The approach combined model tracking control and reference model adaptive control together, which highly reduced attitude tracking error and improved stability margin of the closed-loop system, and was successfully applied in flight control simulation and flight tests of the vehicle. Martin P and Tung C. Performance and flow field measurements on a 10-inch ducted rotor VTOL UAV.

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In: IEEE symposium on computational intelligence for security and defense applications (CISDA), Singapore, 2013, pp.51–56. Aruneshwaran R, Jianliang W and Suresh S. Neural adaptive back stepping flight controller for a ducted fan UAV. In: 10th World Congress on intelligent control and automation (WCICA), Singapore, 2012, pp.2370–2375. Nardi F, Rysdykt RT and Calisej AJ. Neural network based adaptive control of a thrust vectored ducted fan.

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