Printed multifunctional skin for aerodynamic structures and associated systems and methods

1. An aerodynamics apparatus, comprising:

an aerodynamic structure having a first surface (ES) exposed to an outside environment (OE), and a second surface (IS) exposed to an inside environment (IE); and

a printed sensor carried by the first surface (ES) of the aerodynamic structure;

electronics carried by the second surface (IS) of the aerodynamic structure; and

at least one printed conductive trace carried by the first surface (ES) and the second surface (IS), wherein the at least one printed conductive trace electrically connects the printed sensor with the electronics.

2. The apparatus of claim 1 , wherein the aerodynamic structure is a first aerodynamic structure, the apparatus further comprising:

a second aerodynamic structure connected with the first aerodynamic structure, wherein the at least one printed conductive trace is at least partially routed within a spacing between the first aerodynamic structure and the second aerodynamic structure.

3. The apparatus of claim 2 , wherein the at least one printed conductive trace is a first printed conductive trace, the apparatus further comprising:

a third aerodynamic structure connected with the first aerodynamic structure; and

a second printed conductive trace that is at least partially routed within a spacing between the first aerodynamic structure and the third aerodynamic structure.

4. The apparatus of claim 3 , further comprising at least one printed element selected from a group consisting of a printed actuator, an antenna, a transducer, and a functional coating, wherein the second printed conductive trace is electrically connected to the at least one printed element.

5. The apparatus of claim 1 , wherein the aerodynamic structure includes at least one via connecting the first surface (ES) and the second surface (IE) of the aerodynamic structure, and wherein the at least one via includes an electrically conductive element that electrically connects the printed sensor on the first surface (ES) with the electronics on the second surface (IE).

6. The apparatus of claim 5 , wherein the electrically conductive element is an electrically conductive pin.

7. The apparatus of claim 5 , wherein the electrically conductive element is a 3D-printed trace.

8. The apparatus of claim 1 , wherein the aerodynamic structure is a canopy of an airplane.

9. The apparatus of claim 1 , wherein the aerodynamic structure is a window panel.

10. The apparatus of claim 1 , wherein the aerodynamic structure is an aircraft structure.

11. The apparatus of claim 10 , wherein the aircraft structure is an element of an unmanned airplane.

12. The apparatus of claim 1 , wherein the aerodynamic structure is an element of a pump, a wind turbine, an air fan, a submarine, a ship, an engine, a prosthetics, a windshield, a car, a helmet, a goggle or glasses.

13. A method of instrumenting an aerodynamic structure, comprising:

providing the aerodynamic structure having a first surface (ES) and a second surface (IS) opposite from the first surface;

printing a sensor over the first surface (ES);

adding electronic components to the second surface (IS); and

printing conductive traces over the first surface (ES) and the second surface (IS), wherein the conductive traces electrically connect the sensor with the electronic components;

wherein the first surface (ES) is exposed to an outside environment (OE), and the second surface (IS) is exposed to an inside environment (IE).

14. The method of claim 13 , further comprising:

printing at least one printed element selected from a group consisting of a printed actuator, an antenna, a transducer, and a functional coating over the first surface (ES) of the aerodynamic structure; and

electrically connecting the actuator to the electronic components with the printed conductive traces.

15. The method of claim 14 , further comprising:

printing the sensor and the actuator over a foil by an electronics printer using additive manufacturing; and

adhering the foil to the first surface (ES) of the aerodynamic structure.

16. The method of claim 13 , wherein the aerodynamic structure is an element of a pump, a wind turbine, an air fan, a submarine, a ship, an engine, a prosthetics, a windshield, a car, a helmet, a goggle or glasses.

17. The method of claim 14 , wherein the sensor is selected from a group consisting of a pressure sensor, a temperature sensor, a heat flux sensor, a strain sensor, an ice sensor, a strain transducer, and an RF antenna; and the actuator is selected from a group consisting of a heater, a piezoelectric transducer, a functional coating, an ionic actuator, a plasma actuator, and a miniature air blower.

18. The method of claim 14 , wherein the aerodynamic structure is a canopy of an airplane.

19. The method of claim 14 , wherein the aerodynamic structure is a first aerodynamic structure, the method further comprising:

connecting a second aerodynamic structure with the first aerodynamic structure, wherein the at least one printed conductive trace is at least partially routed within a spacing between the first aerodynamic structure and the second aerodynamic structure.

20. The method of claim 14 , further comprising:

forming at least one via in the aerodynamic structure, wherein the at least one via connects the first surface (ES) and the second surface (IS) of the aerodynamic structure; and

placing an electrically conductive element inside the at least one via, wherein the electrically conductive element electrically connects the printed sensor on the first surface (ES) with the electronic components on the second surface (IS).

21. The method of claim 13 , wherein the aerodynamic structure is an element of an unmanned aircraft.