6 results about "Side-stick" patented technology

The present application relates to the technical field of aircraft operating mechanism, in particular to a drive-control integrated aircraft side stick operating mechanism, which comprises a box body, a controller and a driver, a roll transmission shaft is rotatably supported in the box body, a U-shaped decoupling mounting seat is fixedly connected to one end of the roll transmission shaft, a pitch shaft is horizontally supported in the U-shaped decoupling mounting seat, a base is fixedly sleeved on the pitch shaft, a handle connecting rod and a handle assembly are sequentially connected to the upper end of the base, a roll motor drives a rocker arm I through a rocker arm II and a transmission connecting rod I, the rocker arm I is hinged to the roll transmission shaft, a pitch motor drives a fixed head through a rocker arm III and a transmission connecting rod II, and the fixed head is fixedly arranged at the end of the pitch shaft. The present application provides a drive-control integrated aircraft side stick operating mechanism with high integration, ultra-small volume, double-channel synchronous force sensing, microsecond-level real-time bus communication and plug-and-play, which is particularly suitable for the demand of high-fidelity, high-reliability and small-sized operating device of high-level flight simulator.

The invention belongs to the technical field of aircraft cockpit side lever devices, and discloses an aircraft miniaturized four-shaft side lever which comprises a handle, a yawing rotating shaft, a pitching rotating shaft and a rolling rotating shaft, the handle is provided with a shifting wheel, and control input of a vertical shaft can be achieved. The transverse rolling rotating shaft comprises a pitching rotating shaft assembly and a pair of deep groove ball bearings and can rotate around the transverse rolling bearing installed on the shell. The pitching rotating shaft comprises a yaw rotating shaft assembly and a pair of deep groove ball bearings and can rotate around a pitching bearing installed on the universal joint frame. The yaw rotating shaft comprises a handle assembly, a pair of angular contact ball bearings and a needle bearing and can rotate around the center line of a bearing chamber on a shell of the yaw shaft. The problems that an existing aircraft side rod is difficult to miniaturize and cannot be integrated with other aircraft attitude control equipment such as pedals are solved, and light weight and miniaturization are considered on the basis of increasing the degree of freedom.

The utility model relates to an airplane side rod device and an airplane. The aircraft side rod device comprises a side rod body, a sliding structure and a locking structure, wherein the side rod body is provided with an operating handle; the sliding structure comprises a first sliding part and a second sliding part which are in sliding fit, the first sliding part is arranged on the side rod body, the second sliding part is used for being arranged on an instrument desk of an airplane, and in the relative sliding process of the first sliding part and the second sliding part, the side rod body can move in the first direction so that the side of a pilot can get close to or get away from the pilot; the locking structure is used for unlocking or locking the first sliding piece and the second sliding piece. The aircraft side lever device can provide comfortable control experience for pilots with different heights, and the problem of hand fatigue of short or high pilots in the driving process is effectively relieved.