Non-contact power supply and data transfer on aerial vehicles

1. An aircraft comprising:

a first structure on the aircraft including a transmitter, a first surface, and a first coil conformed to a shape of the first surface or embedded within the first structure, wherein the first structure includes a plurality of first coils including the first coil;

a second structure on the aircraft including circuitry, a second surface, and a second coil conformed to a shape of, or embedded within, the second surface, the second structure on the aircraft configured to couple to the first structure on the aircraft such that the first coil is aligned with the second coil to enable inductive coupling between the first coil and the second coil, wherein the transmitter is configured to transmit control signals to the circuitry via the first coil and the second coil; and

a processor electrically coupled to the plurality of first coils, wherein the processor is configured to identify a first component of the circuitry based on an impedance of a particular first coil of the plurality of first coils.

2. The aircraft of claim 1 , wherein the processor is configured to detect a configuration of the second structure based on which coils of the plurality of first coils are inductively coupled to corresponding coils of one or more second coils of the second structure, wherein the one or more second coils include the second coil.

3. The aircraft of claim 2 , wherein the configuration indicates a number of electrical components in the second structure.

4. The aircraft of claim 2 , wherein the control signals are generated based on the configuration.

5. The aircraft of claim 1 , wherein the first component is a de-icing system.

6. The aircraft of claim 1 , wherein the second structure further includes a third surface and a third coil conformed to a shape of, or embedded within the third surface, the aircraft further comprising a third structure including a fourth surface and a fourth coil conformed to a shape of, or embedded within the fourth surface, the third structure configured to couple to the second structure such that the third coil is aligned with the fourth coil to enable inductive coupling between the third coil and the fourth coil.

7. The aircraft of claim 6 , wherein the circuitry includes a motor, and wherein the motor is configured to manipulate the third structure responsive to the control signals.

8. The aircraft of claim 6 , wherein the third structure includes a wing flap.

9. The aircraft of claim 8 , wherein the control signals are based on a roll rate of the wing flap.

10. A method of configuring an aerial vehicle, the method comprising:

mating a first surface of a first structure of the aerial vehicle and a second surface of a second structure of the aerial vehicle such that a first coil conformed to a shape of the first surface or embedded within the first structure is aligned with a second coil conformed to a shape of the second surface or embedded within the second structure, the first structure including a transmitter, the second structure including circuitry, wherein the first structure includes a plurality of first coils including the first coil;

causing a signal to be applied to the plurality of first coils or to the second coil such that the first coil and the second coil are inductively coupled;

identifying a first component of the circuitry based on an impedance of a particular first coil of the plurality of first coils; and

transmitting a control signal from the transmitter to the first component via the first coil and the second coil.

11. The method of claim 10 , further comprising detecting a parameter associated with the first coil.

12. The method of claim 11 , wherein the parameter corresponds to an effective impedance, a frequency of a time-varying signal, or a combination thereof.

13. The method of claim 11 , further comprising configuring a system of the aerial vehicle based on the parameter.

14. The method of claim 10 , wherein the first structure includes a fuselage of the aerial vehicle and the second structure includes a wing of the aerial vehicle.

15. The method of claim 10 , further comprising:

detecting a parameter associated with a feedback signal transmitted by the second coil in response to application of the signal to the second coil; and

determining whether the first structure and the second structure are mated and aligned based on the parameter.

16. A method of manufacturing an aerial vehicle, the method comprising:

forming a first coil conformed to a shape of a first surface of, or embedded within, a first structure of the aerial vehicle using a first direct write technique, the first structure including a transmitter electrically coupled to the first coil, wherein the first structure includes a processor electrically coupled to the transmitter, and wherein the first structure includes a plurality of first coils including the first coil, the plurality of first coils electrically coupled to the processor; and

forming a second coil conformed to a shape of a second surface of, or embedded within, a second structure of the aerial vehicle using a second direct write technique, the second structure configured to couple to the first structure such that the first coil is aligned with the second coil to enable inductive coupling between the first coil and the second coil, the second structure including circuitry electrically coupled to the second coil, wherein the transmitter is configured to transmit control signals to the circuitry via the first coil and the second coil, and wherein the processor is configured to identify a first component of the circuitry based on an impedance of a particular first coil of the plurality of first coils.

17. The method of claim 16 , wherein the first structure includes a fuselage of the aerial vehicle and the second structure includes a wing of the aerial vehicle.

18. The method of claim 16 , further comprising hermetically sealing the first coil and hermetically sealing the second coil.

19. The method of claim 16 , wherein the first direct write technique is a same technique as the second direct write technique.

20. The method of claim 16 , wherein the first direct write technique is a different technique than the second direct write technique.