SYSTEM FOR COMPENSATING AERIAL VEHICLE ATTITUDE DISTURBANCES
A method for compensating disturbances in an aerial vehicle having a plurality of thrusters, the disturbances caused by a payload rotating about one or more axes and coupled to the aerial vehicle, the method including the steps of determining aerial vehicle parameters; determining payload parameters comprising physical parameters and dynamic parameters; determining a preferred orientation of the aerial vehicle based on the aerial vehicle parameters and operational instructions; determining a corrective input based on aerial vehicle parameters, payload parameters, and actual orientation feedback; determining an operation of one or more of the plurality of thrusters based on the corrective input and the preferred orientation, then controlling an output of one or more of the plurality of thrusters accordingly; and determining an actual orientation of the aerial vehicle and generating the actual orientation feedback.
1 . A method for compensating disturbances in an aerial vehicle having a plurality of thrusters, the disturbances caused by a payload rotating about one or more axes and coupled to the aerial vehicle, the method comprising the steps of:
a. determining aerial vehicle parameters;
b. determining payload parameters comprising physical parameters and dynamic parameters;
c. determining a preferred orientation of the aerial vehicle based on the aerial vehicle parameters and operational instructions;
d. determining a corrective input based on aerial vehicle parameters, payload parameters, and actual orientation feedback;
e. determining an operation of one or more of the plurality of thrusters based on the corrective input and the preferred orientation, then controlling an output of one or more of the plurality of thrusters accordingly; and
f. determining an actual orientation of the aerial vehicle and generating the actual orientation feedback.
2 . The method of claim 1 , wherein the payload rotates about a first axis and the payload includes a mechanism rotating about a second axis orthogonal to the first axis.
3 . The method of claim 2 , wherein the payload is a LiDAR system.
4 . The method of claim 1 , wherein aerial vehicle parameters comprise physical parameters comprising one or more of spatial dimensions, morphology, weight-related properties, and material properties.
5 . The method of claim 1 , wherein aerial vehicle parameters comprise dynamic parameters comprising one or more of electronic specifications, power source specifications, and motor characteristics.
6 . The method of claim 1 , wherein the thrusters are propellers driven by motors.
7 . The method of claim 1 , wherein dynamic payload parameters comprise torque generated by single or multi-axis angular momentum created by the payload.