Air-conditioning system with a redundant feed of supply air

1. An aircraft system, comprising:

a first bleed air system supplying bleed air to a first pack via a first line;

a second bleed air system supplying bleed air to a second pack via a second line;

a connection line coupled between the first line and the second line, the connection line including a bleed air valve;

a common mixing chamber receiving air treated by the first and second packs;

a first redundant valve system coupled in the first line downstream of the connection line and upstream of the first pack, the first redundant valve system including a first electrical flow control valve (EFCV), which only provides electrical flow control, and a first pneumatic flow control valve (PBV), which only provides pneumatic flow control, arranged for air flow control in a parallel connection, the EFCV comprising an electrically-controlled actuator unit and a flap unit which is set via a pressure membrane, and the PBV comprising a pneumatically-controlled actuator unit and a flap unit which is set via a pressure membrane; and

a second redundant valve system coupled in the second line downstream of the connection line and upstream of the second pack, the second redundant valve system including a second EFCV, which only provides electrical flow control, and a second PBV, which only provides pneumatic flow control, arranged for air flow control in a parallel connection,

wherein if the EFCV fails, the flap unit of the EFCV is closed and the PBV is opened.

2. The aircraft system of claim 1 , further comprising an auxiliary power unit (APU) configured to switch the bleed air valve, where the APU provides ground air supply.

3. The aircraft system of claim 2 , wherein air flow for the packs is controlled by the first and second electrical flow control valves (EFCVs) in operation.

4. The aircraft system of claim 3 , wherein on a failure of the first electrical flow control valve (EFCV), a solenoid connected to the first pneumatic flow control valve (PBV) activates the first PBV, the air flow for the first pack being controlled by the first PBV.

5. The aircraft system of claim 1 , wherein the first and second PBVs are actuated pneumatically.

6. The aircraft system of claim 5 , wherein the first and second PBVs are each actuated by a pneumatically-controlled pressure membrane.

7. The aircraft system in accordance with claim 4 , wherein the air flow through the first and second electrical flow control valves (EFCVs) can be measured continuously via pressure measurements in a Venturi nozzle provided in a line of the aircraft system.

8. The aircraft system in accordance with claim 7 , wherein an air treatment device is connected in front of each electrical flow control valve (EFCV).

9. The aircraft system in accordance with claim 8 , wherein the air treatment device is an ozone converter.

10. The aircraft system in accordance with claim 8 , wherein the air treatment device is a device for the elimination of volatile organic compounds.

11. The aircraft system in accordance with claim 8 , wherein an air feed line for each pneumatic flow control valve (PBV) is led past the air treatment device connected in front of the electrical flow control valve (EFCV) that is arranged in parallel with that PBV.

12. The aircraft system in accordance with claim 11 , wherein the air feed line for each pneumatic flow control valve (PBV) branches off after the air treatment device connected in front of the electrical flow control valve (EFCV) that is arranged in parallel with that PBV in the flow direction.

13. The aircraft system in accordance with claim 1 , wherein each pneumatic flow control valve (PBV) controls to a previously fixed pressure level in response to flow resistance of the pack that is downstream of that PBV.