俯仰倾转机构和飞行器

Abstract

本申请公开了一种俯仰倾转机构和飞行器，属于飞行器倾转机构技术领域，主要目的是提高俯仰倾转机构的运行可靠性，进而确保飞行器飞行安全。本申请的主要技术方案为：该俯仰倾转机构包括主动臂、拉杆、从动臂和俯仰轴；所述主动臂的一端与所述拉杆的一端相铰接，所述拉杆的另一端与所述从动臂的一端相铰接，所述从动臂的另一端固定套设于所述俯仰轴上。

Claims

1. A pitch and tilt mechanism, characterized in that, It includes an active arm, a pull rod, a driven arm, and a pitch axis; one end of the active arm is hinged to one end of the pull rod, the other end of the pull rod is hinged to one end of the driven arm, and the other end of the driven arm is fixedly sleeved on the pitch axis.

2. The pitch tilt mechanism of claim 1, wherein, The length of the pull rod is adjustable.

3. The pitch-tilt mechanism of claim 2, wherein, The pull rod includes a rod body and two rod end joint bearings; the rod body is provided with positive and negative thread sections, and the two rod end joint bearings are respectively threaded to the positive and negative thread sections at both ends of the rod body.

4. The pitch-tilt mechanism of claim 1, wherein, It also includes a tilt motor; the output shaft of the tilt motor is fixedly connected to the end of the active arm away from the pull rod, and the tilt motor is used to drive the active arm to swing, so as to drive the driven arm and the pitch axis to rotate through the pull rod.

5. The pitch-tilt mechanism of claim 4, wherein, It also includes a motor mount; the tilting motor is fixedly mounted on the motor mount, which is used for external fixation.

6. The pitch tilt mechanism of claim 5, wherein, The motor base includes a motor mounting part and a limiting support part; the motor mounting part is used to connect with the tilting motor, and the limiting support part is located on the axial outside of the output shaft of the tilting motor to radially support the active arm.

7. The pitch-tilt mechanism of claim 6, wherein, The limiting support is provided with a mounting hole, and a bearing is provided in the mounting hole; a bushing is fixedly provided at one end of the active arm that is connected to the output shaft of the tilting motor and on the side away from the tilting motor. The bushing is coaxially arranged with the output shaft of the tilting motor, and the bushing passes through the inside of the bearing and can rotate relative to the bearing.

8. The pitch-tilt mechanism of claim 7, wherein, It also includes fasteners; a through hole is provided at the center of the bushing, and a threaded assembly hole is provided at the center of the output shaft of the tilt motor. The fasteners are used to pass through the through hole and be threaded into the threaded assembly hole.

9. The pitch-tilt mechanism of claim 1, wherein, It also includes an angle detection component, which includes a magnetic ring and a magnetic encoder. The magnetic ring is fixedly sleeved on the pitch axis, and the magnetic encoder cooperates with the magnetic ring. The magnetic encoder is used to sense the change in magnetic flux during the rotation of the magnetic ring in order to collect the angular position signal of the pitch axis in real time.

10. An aircraft, characterized in that Includes the pitch and tilt mechanism as described in any one of claims 1 to 9.

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