Fast attitude error correction

1. An aerial vehicle platform comprising:

an aerial vehicle;

a gimbal coupled to the aerial vehicle;

a camera mounted to the gimbal; and

an attitude sensing system comprising:

an inertial measurement unit including one or more gyroscopes to generate a sensed attitude and one or more accelerometers to generate a sensed acceleration vector, the inertial measurement unit to combine the sensed attitude with an attitude adjustment value to generate an adjusted sensed attitude;

an attitude correction determination module to generate an estimated attitude from the sensed acceleration vector and to generate an attitude correction factor based on a difference between the estimated attitude and the adjusted sensed attitude;

a scaling factor module to detect, from the sensed acceleration vector, a stability measure of the inertial measurement unit and to generate a scaling factor based at least in part on the stability measure; and

an attitude estimate alteration module to combine the correction factor and the scaling factor to generate an attitude estimate adjustment value.

2. The aerial vehicle platform of claim 1 , wherein the attitude sensing system further comprises:

a gyroscope saturation detection module to detect a saturation condition of the one or more gyroscopes and to generate a saturation condition signal indicative of the saturation condition; and

wherein the scaling factor module generates the scaling factor based in part on the saturation condition signal.

3. The aerial vehicle platform of claim 1 , wherein the gyroscope saturation detection module outputs the saturation condition signal indicative of the saturation detection when the sensed attitude reaches a predefined maximum output value.

4. The aerial vehicle platform of claim 1 , wherein the scaling factor module detects the stability measure by determining a magnitude similarity between the sensed acceleration vector and a gravity vector, determining a directional stability based on a change in direction of the sensed acceleration vector over a fixed time range, and determining the stability measure based on the magnitude similarity and the directional stability.

5. The aerial vehicle platform of claim 1 , wherein the scaling factor increases when motion of the inertial measurement unit decreases and wherein the scaling factor decreases when motion of the inertial measurement unit increases.

6. The aerial vehicle platform of claim 1 , the attitude correction determination module stores a history of estimated attitudes from a history of sensed acceleration vectors and stores a history of adjusted sensed attitudes, and the attitude correction determination module generates the attitude correction factor based on an average difference between the history of estimated attitudes and the history of adjusted sensed attitudes.

7. The aerial vehicle platform of claim 1 , wherein the attitude sensing system is integrated with the gimbal.

8. The aerial vehicle platform of claim 1 , wherein the attitude sensing system is integrated with the camera.

9. An attitude sensing system comprising:

an inertial measurement unit including one or more gyroscopes to generate a sensed attitude and one or more accelerometers to generate a sensed acceleration vector, the inertial measurement unit to combine the sensed attitude with an attitude adjustment value to generate an adjusted sensed attitude;

an attitude correction determination module to generate an estimated attitude from the sensed acceleration vector and to generate an attitude correction factor based on a difference between the estimated attitude and the adjusted sensed attitude;

a gyroscope saturation detection module to detect a saturation condition of the one or more gyroscopes and to output a saturation condition signal indicative of the saturation condition;

a scaling factor module to detect, from the sensed acceleration vector, a stability measure of the inertial measurement unit and to output a scaling factor based on the stability measure; and

an attitude estimate alteration module to combine the correction factor and the scaling factor to generate an attitude estimate adjustment value.

10. The attitude sensing system of claim 9 , further comprising:

a gyroscope saturation detection module to detect a saturation condition of the one or more gyroscopes and to generate a saturation condition signal indicative of the saturation condition; and

wherein the scaling factor module generates the scaling factor based in part on the saturation condition signal.

11. The aerial vehicle platform of claim 1 , wherein the gyroscope saturation detection module outputs the saturation condition signal indicative of the saturation detection when the sensed attitude reaches a predefined maximum output value.

12. The attitude sensing system of claim 9 , wherein the scaling factor module detects the stability measure by determining a magnitude similarity between the sensed acceleration vector and a gravity vector, determining a directional stability based on a change in direction of the sensed acceleration vector over a fixed time range, and determining the stability measure based on the magnitude similarity and the directional stability.

13. The attitude sensing system of claim 9 , wherein the scaling factor increases when motion of the inertial measurement unit decreases and wherein the scaling factor decreases when motion of the inertial measurement unit increases.

14. The attitude sensing system of claim 9 , the attitude correction determination module stores a history of estimated attitudes from a history of sensed acceleration vectors and stores a history of adjusted sensed attitudes, and the attitude correction determination module generates the attitude correction factor based on an average difference between the history of estimated attitudes and the history of adjusted sensed attitudes.

15. A method for sensing attitude comprising:

sensing, by one or more gyroscopes, a sensed attitude;

combining by an inertial measurement unit, the sensed attitude with an attitude adjustment value to generate an adjusted sensed attitude;

generating, by one or more accelerometers, a sensed acceleration vector;

generating, by an attitude correction determination module, an estimated attitude from the sensed acceleration vector;

generating, by the attitude correction determination module, an attitude correction factor based on a difference between the estimated attitude and the adjusted sensed attitude;

detecting, by a scaling factor module, a stability measure of the inertial measurement unit based on the sensed acceleration vector and generating a scaling factor based on the stability measure; and

combining, by an attitude estimate alteration module, the correction factor and the scaling factor to generate an attitude estimate adjustment value.

16. The method of claim 15 , further comprising:

detecting, by a gyroscope saturation module, a saturation condition of the one or more gyroscopes and generating a saturation condition signal indicative of the saturation condition,

wherein generating the scaling factor is further based on the saturation condition signal.

17. The method of claim 16 , wherein detecting the saturation condition comprises:

detecting that the sensed attitude reaches a predefined maximum output value.

18. The method of claim 15 , wherein detecting the stability measure comprises:

determining a magnitude similarity between the sensed acceleration vector and a gravity vector;

determining a directional stability based on a change in direction of the sensed acceleration vector over a fixed time range; and

determining the stability measure based on the magnitude similarity and the directional stability.

19. The method of claim 15 , wherein the scaling factor increases when motion of the inertial measurement unit decreases and wherein the scaling factor decreases when motion of the inertial measurement unit increases.

20. The method of claim 15 , further comprising:

storing, by the attitude correction determination module, a history of estimated attitudes from a history of sensed acceleration vectors;

storing a history of adjusted sensed attitudes; and

wherein generating the correction factor comprises determining an average difference between the history of estimated attitudes and the history of adjusted sensed attitudes.