Miniature stabilized unmanned aerial vehicle gimbal
Embodiments discussed herein provide improved control of an unmanned aerial vehicle camera gimbal. In some embodiments, a linear control circuit is described that uses an operational amplifier that allows the system to retain its passive isolation of high frequency disturbances.
1. A gimbal with a plurality of axes for stabilizing an image sensor, the gimbal comprising:
a plurality of rotationally positionable motors, each of the plurality of rotationally positionable rotors configured to drive rotation about an axis of the plurality of axes, each of the plurality of motors comprising:
a stator; and
a plurality of magnets positioned radially about the stator;
a first inertial measurement sensor fixed relative to an image sensor;
a second inertial measurement sensor fixed relative to a fuselage;
a gimbal control circuit functionally connected to the first inertial measurement sensor and to the second inertial sensor, the plurality of motors configured for control based on input from both the first inertial measurement sensor and the second inertial measurement sensor; and
a high bandwidth operational amplifier circuit for driving each motor.
2. A gimbal with a plurality of axes for stabilizing an image sensor, comprising:
a plurality of rotational permanent-magnet motors, each of the plurality of motors configured to induce rotation about one of a plurality of axes;
a first inertial measurement sensor associated with an image sensor;
a second inertial measurement sensor associated with a fuselage;
a control circuit configured to control the plurality of plurality of motors based on input from the first and second inertial measurement sensors; and
a high bandwidth operational amplifier circuit for driving each motor.
3. An unmanned aerial vehicle (UAV), comprising:
a fuselage;
a first inertial measurement sensor associated with the fuselage;
an image sensor;
a second inertial measurement sensor associated with the image sensor; and
a gimbal secured relative to the fuselage and configured to stabilize the image sensor, the gimbal comprising a plurality of motors, each motor configured to induce rotation about one of a plurality of axes;
a control circuit configured to control the plurality of plurality of motors based on input from the first and second inertial measurement sensors; and
a high-bandwidth operational amplifier circuit configured to drive the plurality of motors.
4. The UAV of claim 3 , wherein the plurality of motors comprises a plurality of permanent-magnet rotational motors.
5. The UAV of claim 3 , wherein the fuselage comprises a concave region, and wherein the gimbal is disposed at least partially within the concave region of the fuselage.
6. The UAV of claim 3 , wherein the gimbal comprises an optically clear shield, and wherein the gimbal is disposed within the optically clear shield.
7. The UAV of claim 3 , wherein the gimbal comprises a two-axis gimbal.
8. The UAV of claim 7 , wherein the plurality of motors comprises:
a pitch stage motor configured to control the rotation of a pitch stage; and
a roll stage motor configured to control the rotation of a roll stage.
9. The UAV of claim 8 , wherein the pitch stage is rotatably coupled to the fuselage, wherein the roll stage is rotatably coupled to the pitch stage, and wherein the image sensor is supported by the roll stage.
10. The UAV of claim 3 , wherein the gimbal comprises a three-axis gimbal.
11. The gimbal of claim 2 , wherein the gimbal comprises a two-axis gimbal.
12. The gimbal of claim 2 , wherein the gimbal comprises a three-axis gimbal.
13. The gimbal of claim 2 , wherein the gimbal comprises:
a first stage rotatably coupled to a gimbal mount, wherein the plurality of motors comprises a first motor configured to control rotation of the first stage relative to the gimbal mount; and
and a second stage rotatably coupled to the first stage, wherein the plurality of motors further comprises a second motor configured to control rotation of the second stage relative to the first stage.
14. The gimbal of claim 12 , wherein the image sensor is supported by the second stage.
15. The gimbal of claim 13 , wherein the first inertial measurement sensor is disposed within the fuselage, and wherein the second inertial measurement sensor is supported by the second stage.
16. The gimbal of claim 1 , wherein the gimbal comprises a two-axis gimbal.
17. The gimbal of claim 1 , wherein the gimbal comprises a three-axis gimbal.
18. The gimbal of claim 1 , wherein the gimbal comprises:
a first stage rotatably coupled to a gimbal mount, wherein the plurality of motors comprises a first motor configured to control rotation of the first stage relative to the gimbal mount; and
and a second stage rotatably coupled to the first stage, wherein the plurality of motors further comprises a second motor configured to control rotation of the second stage relative to the first stage.
19. The gimbal of claim 18 , wherein the image sensor is supported by the second stage.
20. The gimbal of claim 18 , wherein at least a portion of the gimbal control circuit is not supported by either the first stage or the second stage.