Heating system for an aircraft or spacecraft

• US 20140319115A1
• Filed: 11/27/2012
• Published: 10/30/2014
• Est. Priority Date: 12/07/2011
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Altay, Mehmet
• Granted Patent: US 9,380,648 B2
• Time in Patent Office: Days
• US Class Current: 219/202
• CPC Class Codes: B64C 1/1453 Drain masts
• CPC Class Codes: B64C 1/18 Floors
• CPC Class Codes: B64D 13/08 the air being heated or cooled
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64G 1/428 Power distribution and management
• CPC Class Codes: B64G 1/50 for temperature control
• CPC Class Codes: H04B 2203/5458 Monitor sensor; Alarm systems
• CPC Class Codes: H04B 3/548 the power on the line being DC arrangements for feeding power H04L12/10; extracting feeding power from signals H04L25/02
• CPC Class Codes: H05B 1/0236 for vehicles

Abstract

A heating system for an aircraft or spacecraft with a control device which includes at least one power line data transmission transceiver and one sensor controller, and at least one remote component which has a sensor element and a heating element, the at least one power line data transmission transceiver being connected to the at least one remote component via a connecting cable, the control device being designed to supply the at least one heating element with power via the connecting cable and the sensor controller being designed to exchange first control signals with the sensor element via the connecting cable.

Claims

1-10. -10. (canceled)

11. A heating system for an aircraft or spacecraft, comprising:

a control device, which comprises at least one power line data transmission transceiver and a sensor controller; and

at least one remote component, which comprises a sensor element and a heating element,

wherein the at least one power line data transmission transceiver is connected to the at least one remote component via a connecting cable,

wherein the control device is designed to supply the at least one heating element with power via the connecting cable, and

wherein the sensor controller is designed to exchange first control signals with the sensor element via the connecting cable.

12. The heating system according to claim 11, wherein the sensor controller is designed to communicate with the sensor element by means of a power line data transmission system.

13. The heating system according to claim 11, wherein the control device comprises a heating controller which is designed to exchange second control signals with the heating element via the connecting cable.

14. The heating system according to claim 11, wherein the sensor element is a temperature sensor and wherein the first control signals comprise temperature measurement values in the vicinity of the remote components.

15. The heating system according to claim 14, wherein the remote component comprises an evaluation circuit which is configured to evaluate the temperature measurement values recorded by the temperature sensor.

16. A method for operating a heating system for an aircraft or spacecraft, comprising:

supplying a first remote component, which comprises a heating element, with power by a control device via a first connecting cable; and

exchanging control signals between the control device and a sensor element of the first remote component via the first connecting cable.

17. The method according to claim 16, further comprising:

supplying a second remote component, which comprises a heating element, with power by the control device via a second connecting cable; and

exchanging control signals between the control device and a sensor element of the second remote component via the second connecting cable.

18. The method according to claim 16, wherein the sensor element comprises a temperature sensor and wherein exchanging control signals entails exchanging temperature measurement values.

19. An aircraft or spacecraft comprising a heating system, the heating system comprising:

a control device, which comprises at least one power line data transmission transceiver and a sensor controller; and

at least one remote component, which comprises a sensor element and a heating element,

wherein the at least one power line data transmission transceiver is connected to the at least one remote component via a connecting cable,

wherein the control device is designed to supply the at least one heating element with power via the connecting cable, and

wherein the sensor controller is designed to exchange first control signals with the sensor element via the connecting cable.

20. The aircraft or spacecraft according to claim 19, wherein the at least one remote component is a pipe heating component of the aircraft or spacecraft.

21. The aircraft or spacecraft according to claim 19, wherein the at least one remote component is an underfloor heating component of the aircraft or spacecraft.

22. The aircraft or spacecraft according to claim 19, wherein the at least one remote component is a drainage heating component of the aircraft or spacecraft.

23. The aircraft or spacecraft according to claim 19, wherein the at least one remote component is a waste water pipe heating component of the aircraft or spacecraft.