Optical communication bus network for avionic equipment
View Patent ↗An avionic system for an aircraft including at least two pieces of equipment which can exchange information by means of at least one electrical bus for simultaneous bidirectional communication, in which the information can be exchanged between pieces of equipment via an optical bus that can be connected to the electrical interfaces of the equipment. The optical bus of the avionic system includes at least one optical cable having at least one optical fiber and, at each end, a connector having means for converting electrical signals into optical signals and means for converting optical signals into electrical signals. The optical bus is connected to the electrical outlets of existing equipment.
1. An aircraft avionics system comprising:
at least first and second pieces of equipment comprising a first and second bus interface, respectively, configured for exchanging information over at least one electrical bus for simultaneous two-way communication,
at least one two-way optical communication bus, configured to replace the at least one electrical communication bus and connected between the first and second bus interface of the at least first and second pieces of equipment, respectively, for exchanging information between the at least first and second pieces of equipment,
the at least one two-way optical communication bus comprising at least one optical cable having:
a first end comprising:
a first electrooptic converter for converting electrical signals from one of the first and second pieces of equipment into optical signals of a first wavelength λ1, and a second electrooptic converter for converting optical signals of a second wavelength λ2 into electrical signals provided to the one of the first and second pieces of equipment; and
a second end comprising:
a third electrooptic converter for converting electrical signals from other of the first and second pieces of equipment into optical signals of the second wavelength λ2,
a fourth electrooptic converter for converting optical signals of the first wavelength λ1 into electrical signals provided to the other of the first and second pieces of equipment.
2. The avionics system of claim 1 , wherein each of the first and second interface comprises a connector comprising four channels, the four channels comprising two electrical contacts for transmitting electrical signals and two electrical contacts for receiving electrical signals.
3. The avionics system of claim 2 , wherein electronic components of one or more of the electrooptic converters incorporated in a connector comprise at least one conducting wire for connection to an external power supply.
4. The avionics system of claim 2 , wherein at least one of the two electrical contacts for transmitting electrical signals and the two electrical contacts for receiving electrical signals supplies power to an electro-optical converter of the first and third electrooptic converters and an opto-electrical converter of the second and fourth electrooptic converters.
5. The avionics system of claim 4 , wherein at least one of the pieces of equipment includes a decoupler for decoupling the power from the electrical signals, allowing interchangeable use of the at least one electrical bus or the at least one two-way optical communication bus.
6. The avionics system of claim 2 , wherein at least one of the two electrical contacts for transmitting electrical signals supplies power to an electro-optical converter of the first and third electrooptic converters and an opto-electrical converter of the second and fourth electrooptic converters.
7. The avionics system of claim 6 , wherein at least one of the pieces of equipment comprises an electrical power supply for delivering power to the at least one of the two electrical contacts for transmitting signals.
8. The avionics system as claimed in claim 6 , wherein at least one of the first and second pieces of equipment comprises at least one socket for the at least one electrical bus and for the at least one two way optical communication bus, wherein the power is superposed on a digital signal on the at least one of the two electrical contacts for transmitting electrical signals, the socket comprising a decoupler for decoupling the power from the digital signal.
9. The avionics system of claim 2 , wherein at least one of the two electrical contacts for receiving electrical signals supplies power to an electro-optical converter of the first and third electrooptic converters and an opto-electrical converter of the second and fourth electrooptic converters.
10. The avionics system of claim 9 , wherein at least one of the pieces of equipment comprises an electrical power supply for delivering power to the at least one of the two electrical contacts for receiving signals.
11. The avionics system as claimed in claim 9 , wherein at least one of the first and second pieces of equipment comprises at least one socket for the at least one electrical bus and for the at least one two-way optical communication bus, wherein the power is superposed on a digital signal on the at least one of the two electrical contacts for receiving electrical signals, the socket comprising a decoupler for decoupling the power from the digital signal.
12. The avionics system of claim 1 , wherein the at least one two-way optical communication bus comprises:
at the first end of the optical cable, a first connector comprising:
means for holding the optical cable fastened to the first connector in a position of alignment, and
electrical contacts conforming geometrically and electrically to four channel electrical bus contacts; and
at the second end of the optical cable, a second connector comprising:
means for holding the optical cable fastened to the second connector in a position of alignment, and
electrical contacts conforming geometrically and electrically to four channel electrical bus contacts.