![]() Marr, "V/STOL tilt rotor study - A mathematical model for real time flight simulation of the bell 301 tilt rotor research aircraft," NASA-CR-114614, NASA, Apr. Min, "Automated control gain determination using PSO/SQP algorithm," Journal of Aerospace Technology (in Korean), KARI, vol. of the IEEE International Conference on Neural Networks, Perth, Australia, pp. Eberhart, "Particle swarm optimization," Proc. Robb, "Hybrid helicopters: Compounding the quest for speed," Vertiflite, Summer 2006, p. "Sikorsky Breaks 250 KTAS Record," Rotor & Wing. Finnegan, Joy editor-in-chief (1 October 2010).Croft, John, "Sikorsky X2 hits 250kt goal," Flight International.Kim, "Recent world trend in VTOL aircraft development: Good timing for Korean aircraft industry to escape from red ocean," The Journal of Aerospace Industry (in Korean), ISSN 1738-1169, vol. Tahk, "Autonomous waypoint guidance for tilt-rotor unmanned aerial vehicle that has nacelle fixed auxiliary wings," Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 4 Mar. Kang, "Sea wave modeling analysis and simulation for shipboard landing of tilt rotor unmanned aerial vehicle," Journal of KSAS (in Korean), vol. Choi, "Envelop expansion flight test of flight control systems for TR-60 Tilt-rotor UAV," ICCAS 2013, pp. Koo, "Analysis of flight test result for control performance of smart UAV," Journal of Aerospace Technology (in Korean), KARI, vol. The nonlinear simulation results of the guidance control for the preprogrammed mode and point navigation are also presented including automatic take-off and landing in order to prove the full control law. Therefore the speed and altitude hold mode are coupled to each other and are engaged at the same time when an internal pilot engages any of the altitude or speed hold modes. Otherwise, the control parameter for the speed of the helicopter mode is the pitch attitude command and it is transferred to the thrust command in airplane mode. The main control parameter for altitude control of the helicopter mode is thrust command and it is transferred to the pitch attitude command in airplane mode. The outer loops for the hold mode are designed with trial and error methods with linear and nonlinear simulation. The stability margins of the inner loop are presented with the optimization approach. ![]() The nacelle conversion of the original tilt-rotor starts when the airspeed is greater than 30 km/h but its WE variant starts at 0 km/h in order to reduce the drag caused by the high incidence angle of the WE. The conversion corridor and the control moments derivatives between the original tilt-rotor and its variant of the nacelle mounted WE were compared to show the effectiveness of the WE. It consists of a control surface mixer, stability and control augmentation system (SCAS), hold mode for altitude / speed / heading, and a guidance mode for preprogram and point navigation which includes automatic take-off and landing. The results of control law design for a tilt-rotor unmanned aerial vehicle that has a nacelle mounted wing extension (WE) are presented in this paper.
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