An Intermeshing Rotor Helicopter Design and Test

摘要

Central Connecticut State University's (CCSU) Engineering Department is designing and testing a small scaled counter-rotating intermeshing rotor model helicopter to study various rotor shaft lateral tilt angle effects. One of the main purposes of this research is to explore the possibility of increase the helicopter flight envelope by changing the rotor shaft tilt angle without significantly impacting the required rotor lift and power. Three rotor shaft tilt angles and their associated bevel gear train dynamic components were designed and tested. The fuselage was designed by joining two halves of helicopter fuselages using a hinged plate in order to properly simulate each required rotor shaft tilt angle. The tests were conducted by varying engine throttle positions, collective and cyclic control inputs, and blade root end pitch angles. Forty two data points were collected. Both dimensional and non-dimensional performance information were analyzed. The maximum rotor rpm experienced during the test was recorded at 1,433 rpm. At 90% engine throttle control positions, the maximum blade lift obtained during this test, exceeds 20 lbs when the blade root end collective settings were higher than 7.5°. Preliminary results indicated that this was a successful tie down test. This success also extends to functional testing of the helicopter dynamic drive systems, flight control systems, and power generating systems.