A blade actuation system comprises at least one motor coupled to a rotor blade for changing the pitch angle of the rotor blade. The motor is configured to wirelessly communicate with at least one flight control computer to modulate the pitch angle. At least one generator may be mounted on a...
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An electric linear actuator is disposed to pitch a blade of a hingeless, swashplateless rotor in rotary motion. This actuator can be equipped with an electric motor advantageously made fault tolerant by winding the motor for at least 4, 5, 6, 8, or even 12 phases. Rotational motion of ...
This paper introduces a test stand, called Co-Stand, designed to evaluate the performance of the micro aerial robots equipped with the swashplateless mechanisms using ground-based testing, without requiring actual flight tests. The Co-Stand is constructed to collect data on operati...
A main rotor system of an aircraft is provided including a first rotor coupled to a transmission and configured to rotate about an axis in a first direction. A second rotor is similarly coupled to the transmission and is configured to rotate about the axis in a second direction. At least ...
J. Paulos and M. Yim, "Flight performance of a swashplateless micro air vehicle," in 2015 IEEE International Conference on Robotics and Automation (ICRA), Seattle, WA, May 2015, pp. 5284-5289.PAULOS J, YIM M. Flight performance of a swashplate- less micro air vehicle[C]//2015 IEEE ...
A PID loop is implemented for closed loop control of flap amplitude and mean position.;On the hoverstand at 900 RPM, the swashplateless concept is demonstrated. The linear springs used to lower the torsional frequency are shown to have minimum friction during rotation. 1/rev blade pitching of...
A multicyclic controller was implemented with the swashplateless rotor analysis, and the feasibility of trailing-edge flap performing both primary control and active vibration control was examined. Flap control inputs of a swashplateless rotor are presented at several advance ratios. With optimal ...
Shen, J., Chopra, I., and Johnson, W., "Performance of Swashplateless Helicopter with Trailing-Edge Flaps for Primary Flight Control," Journal of the American Helicopter Society, Vol. 55, (4), October 2010.Shen, J., Chopra, I., and J...
A blade actuation system comprises at least one motor coupled to a rotor blade for changing the pitch angle of the rotor blade. The motor is configured to wirelessly communicate with at least one flight control computer to modulate the pitch angle. At least one generator may be mounted on a...