2results about How to "Reduce overall form factor" patented technology

This invention provides a locking and releasing mechanism, method, and aircraft, comprising: a housing, an elastic element fixing rod, a rotating shaft, an assisting elastic element, a locking hook, and a locking force-bearing element. The elastic element fixing rod and the rotating shaft are fixedly disposed at intervals within a receiving cavity. The assisting elastic element is disposed within the receiving cavity, with one end connected to the elastic element fixing rod. The locking hook is disposed within the receiving cavity and is rotatable around the rotating shaft. The locking hook is connected to the other end of the assisting elastic element. The locking hook includes a first locking hook segment, a second locking hook segment, and a third locking hook segment connected in sequence. The locking force-bearing element is movable along the height direction of the housing and can selectively engage with a locking hole. The locking force-bearing element can abut against the first locking hook segment to restrict its rotation. This invention addresses the technical problems of existing locking and releasing mechanisms being overly complex in structure, having numerous operating procedures, and being difficult to quickly disassemble in emergency situations.

The invention provides a high-speed wind tunnel large-amplitude pitching and yawing coupling motion mechanism and a test method, and belongs to the technical field of wind tunnel special tests. The problems that in the prior art, an aircraft disturbs a flow field in a high-speed wind tunnel due to a tail strut, the load of a driving mechanism is increased due to the large size of a moving part, and model regular oscillation is difficult to achieve are solved. Driving shafts at the two ends of a pitching mechanism are installed on the side wall of a wind tunnel and connected with an external driving mechanism, and a yawing mechanism is perpendicularly installed in the middle of the pitching mechanism through a connecting base. The yaw oscillation shaft is connected with the transmission shaft through the bevel gear set, the balance is installed at the front end of the yaw oscillation shaft, and the test model is installed on the balance. A yaw motor in the connecting seat is connected with an inclined speed reducer, and an output shaft of the inclined speed reducer is connected with a transmission shaft. The problems that in the prior art, an aircraft disturbs a flow field in a high-speed wind tunnel due to a tail supporting rod, the load of a driving mechanism is increased due to the large size of a moving part, and model regular oscillation is difficult to achieve are solved.