Canopy transmittal reflectance control and information display

• US 5,790,209 A
• Filed: 02/20/1997
• Issued: 08/04/1998
• Est. Priority Date: 11/10/1994
• Status: Expired due to Fees

• Current Assignee: Grumman Aerospace Corporation (Northrop Grumman Corporation)
• Original Assignee: Northrop Grumman Corporation
• Inventors: Engelhardt, Michel, Schiavone, John M.
• Primary Examiner(s): Gross, Anita Pellman
• Assistant Examiner(s): Parker, Kenneth
• Application Number:
  US08/803,559
• Time in Patent Office: 530 Days
• Field of Search: 349/16, 349/11
• US Class Current: 349/16
• CPC Class Codes: B64C 1/1476 Canopies; Windscreens or similar transparent elements

Abstract

A system for controlling the transmittance of electromagnetic energy through an aircraft cockpit canopy, and more particularly a canopy panel structure incorporating selectively energizable liquid crystals therein for controlling the transmittance of the electromagnetic energy and/or for integrating an information display in the canopy panel structure. Also disclosed is a method for controlling the transmittance of electromagnetic energy through an aircraft cockpit canopy utilizing a liquid crystal arrangement which is incorporated into the canopy panel structure.

Claims

1. A system for controlling the transmittance of electromagnetic energy through an aircraft cockpit canopy comprising:

a) said canopy including a multilayered panel structure having an outer transparent panel surface and an inner transparent panel surface enabling the passage therethrough of incident visible light, and a single layer liquid crystal means which extends over substantially the entire viewing area of the canopy, and interposed between said outer and inner panel surfaces which is electrically controlled to control the amount of light being transmitted through said outer and inner panel surfaces, with the control provided by said single layer liquid crystal means varying from a substantially fully transparent state to a substantially fully opaque state; and

b) means operatively connected to said liquid crystal means for controllably energizing said liquid crystal means to regulate the transmittance of electromagnetic energy through said canopy.

2. A system as claimed in claim 1, wherein said liquid crystal means comprises a film web having liquid crystals embedded therein extending between contiguous surface areas of said outer and inner panel surfaces.

3. A system as claimed in claim 1, wherein said means operatively connected to said liquid crystal means comprises a source of electrical energy for supplying controllable levels of electrical current to selectively energize said liquid crystal means.

4. A system as claimed in claim 2, wherein a first adhesive layer bonds one surface of said liquid crystal film web to the therewith contiguous surface of said outer transparent panel surface, and a second adhesive layer bonds an opposite surface of said liquid crystal film web to the therewith contiguous surface of said inner transparent panel surface.

5. A system as claimed in claim 2, wherein said liquid crystal film web comprises a transparent plastic film substrate.

6. A system as claimed in claim 2, wherein said liquid crystal film web incorporates an integrated optical design to form a display screen to provide information to a pilot in the aircraft cockpit.

7. A system as claimed in claim 6, wherein said information displayable on said display screen is representative of theater-of-operation information.

8. A system as claimed in claim 6, wherein said information displayable on said display screen is representative of a head-up (HUD) information display.

9. A system as claimed in claim 1, wherein activation of said liquid crystal means by said energizing means causes said canopy to become substantially opaque to the transmittance therethrough of electromagnetic energy so as to reduce any vulnerability and susceptibility of a pilot in the aircraft cockpit and of the aircraft to externally incident electromagnetic energy.

10. A system as claimed in claim 1, wherein said energizing means activates said liquid crystal means over at least one controlled surface area of the canopy panel structure.

11. A system as claimed in claim 1, wherein said liquid crystal means convert externally generated laser energies directed against said canopy panel structure into a signal to a pilot of the aircraft in conjunction with information over the coordinates of the incoming laser radiation.

12. A system as claimed in claim 1, wherein activation of said liquid crystal means facilitates reduction in the solar thermal loading of the cockpit so as to reduce heat loading on an environmental control system of the aircraft.

13. A system for controlling the transmittance of electromagnetic energy through a canopy for a aircraft comprising:

a) multilayered panel structure having an outer transparent panel surface and an inner transparent panel surface enabling the passage therethrough of incident visible light, and a single layer liquid crystal means which extends over substantially the entire veiwing area of the canopy, and interposed between said outer and inner panel surfaces which is electrically controlled to control the amount of light being transmitted through said outer and inner panel surfaces, with the control provided by said single layer liquid crystal means varying from a substantially fully transparent state to a substantially fully opaque state; and

b) means operatively connected to said liquid crystal means for controllably energizing said liquid crystal means to regulate the transmittance of electromagnetic energy through said canopy.

14. A system as claimed in claim 13, wherein said liquid crystal means comprises a film web having liquid crystals embedded therein extending between contiguous surface areas of said outer and inner panel surfaces.

15. A system as claimed in claim 13, wherein said means operatively connected to said liquid crystal means comprises a source of electrical energy for supplying controllable levels of electrical current to selectively energize said liquid crystal means.

16. A system as claimed in claim 14, wherein a first adhesive layer bonds one surface of said liquid crystal film web to the therewith contiguous surface of said outer transparent panel surface, and a second adhesive layer bonds an opposite surface of said liquid crystal film web to the therewith contiguous surface of said inner transparent panel surface.

17. A system as claimed in claim 14, wherein said liquid crystal film web comprises a transparent plastic film substrate.

18. A system as claimed in claim 14, wherein said liquid crystal film web incorporates an integrated optical design to form a display screen to provide information to a viewer of said screen.

19. A system as claimed in claim 15, wherein activation of said liquid crystal means by said energizing means causes said panel structure to become substantially opaque to the transmittance therethrough of electromagnetic energy.

20. A system as claimed in claim 13, wherein said energizing means activates said liquid crystal means over at least one controlled surface area of the panel structure.

21. A system as claimed in claim 13, wherein said liquid crystal means convert externally generated laser energies directed against said panel structure into a signal in conjunction with information over the coordinates of the incoming laser radiation.

22. A method of controlling the transmittance of electromagnetic energy through an aircraft cockpit canopy, said canopy including a multilayered panel structure having an outer transparent panel surface and an inner transparent panel surface enabling the passage therethrough of incident visible light;

said method comprising;

a) interposing a single layer liquid crystal means which extends over substantially the entire veiwing area of the canopy, and between said outer and inner panel structures which is electrically controlled to control the amount of light being transmitted through said outer and inner panel surfaces, with the control provided by said single layer liquid crystal means varying from a substantially fully transparent state to a substantially fully opaque state; and

b) operatively connecting said liquid crystal means to an energy source for controllably energizing said liquid crystal means to regulate the transmittance of electromagnetic energy through said canopy.

23. A method as claimed in claim 22, wherein said liquid crystal means comprises embedding liquid crystals in a film web extending between contiguous surface areas of said outer and inner panel surfaces.

24. A method as claimed in claim 22, wherein said energy source supplies electrical energy at controllable levels of electrical current to selectively energize said liquid crystal means.

25. A method as claimed in claim 23, wherein a first adhesive layer bonds one surface of said liquid crystal film web to the therewith contiguous surface of said outer transparent panel surface, and a second adhesive layer bonds an opposite surface of said liquid crystal film web to the therewith contiguous surface of said inner transparent panel surface.

26. A method as claimed in claim 23, wherein said liquid crystal film web comprises a transparent plastic film substrate.

27. A method as claimed in claim 23, wherein said liquid crystal film web has an integrated optical design incorporated therein to form a display screen to provide information to a pilot in the aircraft cockpit.

28. A method as claimed in claim 27, wherein said information displayable on said display screen is representative of theater-of-operation information.

29. A method as claimed in claim 27, wherein said information displayable on said display screen is representative of a head-up (HUD) information display.

30. A method as claimed in claim 22, wherein activation of said liquid crystal means by said energizing source causes said canopy to become substantially opaque to the transmittance therethrough of electromagnetic energy so as to reduce any vulnerability and susceptibility of a pilot in the aircraft cockpit and of the aircraft to externally incident electromagnetic energy.

31. A method as claimed in claim 22, wherein said energizing source activates said liquid crystal means over at least one controlled surface area of the canopy panel structure.

32. A method as claimed in claim 22, wherein said liquid crystal means convert externally generated laser energies directed against said canopy panel structure into a signal to a pilot of the aircraft in conjunction with information over the coordinates of the incoming laser radiation.

33. A method as claimed in claim 22, wherein activation of said liquid crystal means facilitates reduction in the solar thermal loading of the cockpit so as to reduce heat loading on an environmental control system of the aircraft.