The invention relates to a simple rotor mechanism of a coaxial dual-rotor helicopter test stand. The rotor mechanism comprises an inner shaft, an outer shaft, an actuator group, a lower control system, an upper control system, an upper rotor propeller hub and a lower rotor propeller hub, wherein the upper rotor propeller hub comprises a first propeller hub seat, and a first paddle arm arranged on the first propeller hub seat in a full articulation manner; the lower rotor propeller hub comprises a second propeller hub seat and a second paddle arm arranged on the second propeller hub seat in a full articulation manner; the upper control system is connected with the first paddle arm; the lower control system is connected with the second paddle arm; the upper control system is connected with the lower control system via an intermediate draw bar; and the actuator group is connected with the lower control system to control synchronous motion of the first paddle arm and the second paddle arm. The mechanism can achieve collective pitch control and cyclic pitch change of coaxial dual rotors, and effectively achieves various dynamic tests of the helicopter such as upper and lower rotor aerodynamic characteristics of the coaxial dual rotors, dynamic stability of the rotors, and moving part loads of the rotors.
Simple rotor mechanism of coaxial dual-rotor helicopter test stand
2015-09-16
Patent
Electronic Resource
English
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen |
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