Aircraft, tilt driving mechanism and control method thereof

A control method for a tilt driving mechanism mounted on an aircraft, comprising:

• a housing, fixedly mounted on the aircraft;
• a tilt driving mechanism mounted in the housing;
• a mounting seat, flexibly mounted on the housing, the power unit being fixedly mounted on the mounting seat, and the tilt driving mechanism being fixedly connected to the mounting seat, so as to drive the mounting seat to rotate with respect to the housing, wherein the tilt driving mechanism comprises a power source, a first rotation mechanism, and a second rotation mechanism, wherein an output shaft of the power source is connected to the first rotation mechanism, a rotation shaft on the second rotation mechanism is fixedly connected to the mounting seat, and when the output shaft of the power source drives the first rotation mechanism to rotate, the second rotation mechanism and the first rotation mechanism are in a transmission fit;
• and
• wherein the housing comprises a first shell and a second shell that are detachable and cooperate with each other, a receiving cavity is formed between the first shell and the second shell, and the tilt driving mechanism is received in the receiving cavity;
• wherein the control method comprises the steps:
• acquiring data of the first inertia measurement unit and data of the second inertia measurement unit;
• processing the acquired data to obtain a tilt angle of the tilt driving mechanism;
• and
• controlling driving of the tilt driving mechanism, so that the rotation shaft drives the mounting seat to rotate to a set position.

A tilt driving mechanism, mounted on an aircraft to control tilting of a power unit of the aircraft, wherein the tilt driving mechanism comprises:

• a housing, fixedly mounted on the aircraft;
• a driving mechanism, mounted in the housing;
• and
• a mounting seat, flexibly mounted on the housing, the power unit being fixedly mounted on the mounting seat, and the driving mechanism being fixedly connected to the mounting seat, so as to drive the mounting seat to rotate with respect to the housing, wherein the driving mechanism comprises a power source, a first rotation mechanism, and a second rotation mechanism, wherein an output shaft of the power source is connected to the first rotation mechanism, a rotation shaft on the second rotation mechanism is fixedly connected to the mounting seat, and when the output shaft of the power source drives the first rotation mechanism to rotate, the second rotation mechanism and the first rotation mechanism are in a transmission fit, and
• wherein a controller is mounted in the aircraft;
• the power source comprises a driving motor, wherein two ends of a motor shaft of the driving motor are connected to a retarding mechanism and an encoder respectively, and wherein a rotation shaft of the retarding mechanism is the output shaft, and the encoder is electrically connected to the controller.