Method and system for evaluating a structural integrity of an aerial vehicle

1. A method of evaluating a structural integrity of an aerial vehicle comprising one or more engines, said method comprising:

selectively driving said one or more engines of said serial vehicle according to a driving pattern unsuitable to put or maintain the aerial vehicle in flight, wherein the driving pattern comprises one or both of a temporally varied driving pattern, comprising at least two time intervals during which it is characterized be at least one characteristics driving frequency, wherein said characteristic driving frequencies in said at least two time intervals are mutually different from each other, and a multiplexed driving pattern, comprising at least two simultaneously applied driving patterns associated with different respective characteristic driving frequencies;

recording a vibrational response of at least a part of the aerial vehicle to said selective driving of said one or more engines;

determining a plurality of modal parameters of said vibrational response; and

classifying said structural integrity based on a deviation of said plurality of modal parameters from baseline modal parameters for said aerial vehicle.

2. The method of claim 1 , wherein said aerial vehicle comprises a composite fiber supporting structure, and wherein said classifying of said structural integrity comprises classifying a delamination in said composite fiber supporting structure.

3. The method of claim 1 , wherein the one or more selectively driven engines inducing said vibrational response comprise an electric motor, and wherein said driving pattern is characterized, at least in part, by one ore driving voltages applied to said electric motor.

4. The method of claim 1 , wherein said vibrational response is recorded using one or mom sensors incorporated with the aerial vehicle.

5. The method of claim 1 , wherein classifying said structural integrity comprises classifying said structural integrity with a multivariate analyzer comprising a statistical classifier to classify said structural integrity based on said plurality of modal parameters and said baseline modal parameters for said aerial vehicle.

6. The method of claim 5 , wherein said multivariate analyzer classifies said plurality of modal parameters also based on a measured humidity or a measured temperature.

7. The method of claim 5 , wherein the multivariate analyzer comprises a linear discriminant analyzer and the method further comprises obtaining said linear discriminant analyzer by receiving classified baseline modal parameters for a baseline aerial vehicle and determining a projection function and a corresponding classification faction for said received classified baseline modal parameters, said projection function including linear combinations of modal parameters to obtain a plurality of axes, and the classification function comprising a corresponding plurality of thresholds for said as to maximize a selectivity of said linear discriminant analyzer for classifying said structural integrity for the classified baseline modal parameters.

8. The method of claim 1 , wherein the method comprises recording a initial plurality of reference modal parameters for said aerial vehicle and further comprises adjusting a established baseline classifying faction based on a deviation between the initial plurality of reference modal parameters recorded for said aerial vehicle and a plurality of baseline modal parameters of a baseline aerial vehicle.

9. A system for evaluating a structural integrity of a aerial vehicle comprising one or more engines, said system comprising:

a controller configured to selectively drive said one or mom engines of said aerial vehicle according to a driving patter unsuitable to put or maintain the aerial vehicle in flight, wherein the driving pattern comprises one or both of a temporally varied driving pattern, comprising at least two time intervals during which it is characterized by at least one characteristic driving frequency, wherein said characteristic driving frequencies in said at least two time intervals are mutually different from each other, and a multiplexed driving pattern, comprising at least two simultaneously applied driving patterns associated with different respective characteristic driving frequencies;

a sensor configured to record a vibrational response of at least a part of the aerial vehicle to said selective driving of said one or more engines;

a processing unit configured to

determine a plurality of modal parameters of said vibrational response; and

classify said structural integrity based on a deviation of said plurality of modal parameters from reference modal parameters for said aerial vehicle.

10. The system of claim 9 , wherein said aerial vehicle comprises a composite fiber supporting structure, and wherein said processing unit is configured to classify a delamination in said composite fiber supporting structure.

11. The system of claim 9 , wherein the one or more selectively driven engines inducing said vibrational response comprise electric motor, and wherein said driving pattern is characterized, at least in part, by one or more driving voltages applied to said electric motor.

12. The system of claim 9 , wherein said senor is a sensor incorporated with the aerial vehicle.

13. The system of claim 9 , wherein said processing unit implements a multivariate analyzer comprising a statistical classifier to classify said structural integrity based on said plurality of modal parameters and said baseline modal parameters for said aerial vehicle.

14. The system of claim 13 , wherein said multivariate analyzer classifies said plurality of modal parameters also based on a measured humidity or a measured temperature.

15. The system of claim 13 , wherein the multivariate analyzer comprises a linear discriminant analyzer obtained by receiving classified baseline modal parameters for a baseline aerial vehicle and determining a projection function and a corresponding classification function for said received classified baseline modal parameters, said projection function including linear combinations of modal parameters to obtain a plurality of axes, and the classification function comprising a corresponding plurality of thresholds for said axes to maximize a selectivity of said linear discriminant analyzer for classifying said structural integrity for the classified baseline modal parameters.

16. The system of claim 9 , further comprising a storage for parameters of a adjusted baseline classifying faction adjusted based on a deviation between an initially recorded plurality of reference modal parameters for the aerial vehicle and the plurality of baseline modal parameters of a baseline aerial vehicle, and the processing unit is configured to classify said structural integrity of the aerial vehicle with said adjusted baseline classifying faction.

17. The system of claim 9 , with the controller, the sensor and the processing unit incorporated with the aerial vehicle.

18. A non-transitory computer-readable medium storing machine readable instructions which when executed by a processing unit cause the processing unit to implement a method with the steps of:

selectively driving one or mom engines of aerial vehicle according to a driving pattern unsuitable to put or maintain the aerial vehicle in flight, wherein the driving pattern comprises one or both of a temporally varied driving pattern, comprising at least two time intervals during which it is characterized by at least one characteristic driving frequency, wherein said characteristic driving frequencies in said at least two time intervals are mutually different from each other, and a multiplexed driving pattern, comprising at least two simultaneously applied driving patterns associated with different respective characteristic driving frequencies;

recording a vibrational response of at least a part of the aerial vehicle to said selective driving of said one or more engines;

determining a plurality of modal parameters of said vibrational response; and

classifying a structural integrity of the aerial vehicle based on a deviation of said plurality of modal parameters from baseline modal parameters for said aerial vehicle.