Wind tunnel test platform for helicopter maneuvering flight state simulation

• Main Authors: PENG XIANMIN, LUO HUAN, WEI YIBO, ZHANG GUICHUAN, TANG BO, DUAN ZHANGCHENG, TANG MIN, WU JIE, SONG XIN
• Format: Patent
• Language: Chinese; English
• Published: 14.03.2023
• Subjects: AIRCRAFT; AVIATION; COSMONAUTICS; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR; MEASURING; PERFORMING OPERATIONS; PHYSICS; TESTING; TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES; TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR; TRANSPORTING

The invention discloses a wind tunnel test platform for helicopter maneuvering flight state simulation, which comprises a connecting part, a lifting mechanism, an advancing and retreating mechanism, a rolling mechanism, a pitching mechanism and a yawing mechanism, and is characterized in that the connecting part is used for connecting a to-be-tested rotor mechanism; the yawing mechanism comprises a front yawing piece and a rear yawing piece, the front yawing piece is in shaft hinge with the rear yawing piece through a first shaft, the rear yawing piece is in shaft hinge with the lifting mechanism or the advancing and retreating mechanism through a second shaft, the second shaft and the first shaft are both parallel to the Z axis, and the front yawing mechanism is connected with the connecting part through a rolling mechanism and/or a pitching mechanism; the front yawing piece is provided with a first power assembly used for enabling the front yawing piece to rotate with the first shaft as the axis, and the re