AIRCRAFT EMERGENCY POWER SYSTEM

• US 20130076120A1
• Filed: 02/28/2011
• Published: 03/28/2013
• Est. Priority Date: 02/28/2011
• Status: Abandoned Application

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Wagner, Carl A., Krenz, Michael, Jacques, David L.
• Application Number:
  US13/036,968
• Publication Number:
  US 20130076120A1
• Time in Patent Office: Days
• US Class Current: 307/9.1
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 33/00 Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F05D 2270/09 to cope with emergencies

Abstract

An emergency power system for use on an aircraft includes an emergency electrical generator coupled to a mechanical power source for generating emergency electrical power. An electrical power distribution network connects the emergency electrical generator to a plurality of electrical loads. A controller controls the electrical power distribution network to selectively couple and decouple the electrical loads to and from the emergency electrical generator based upon a priority rank assigned to each of the electrical loads.

Claims

1. An emergency power system for use on an aircraft, the emergency power system comprising:

a mechanical power source;

an emergency electrical generator coupled to the mechanical power source for generating emergency electrical power;

a plurality of electrical loads;

an electrical power distribution network connecting the emergency electrical generator to the plurality of electrical loads; and

a controller for controlling the electrical power distribution network to selectively couple and decouple the electrical loads to and from the emergency electrical generator based upon a priority rank assigned to each of the electrical loads.

2. The emergency power system of claim 1, wherein the priority rank represents a relative importance of each electrical load during emergency operation.

3. The emergency power system of claim 1, wherein the controller automatically decouples a lowest priority electrical load from the emergency power generator in anticipation of the electrical power distribution network demanding emergency power in excess of available emergency power.

4. The emergency power system of claim 3, wherein the controller automatically decouples a next lowest priority electrical load from the emergency power generator in anticipation of the electrical power distribution network demanding emergency power in excess of available emergency power even after decoupling the lowest priority electrical load.

5. The emergency power system of claim 1, wherein the controller automatically decouples a lowest priority electrical load from the emergency power generator in anticipation of potential shutdown of the emergency electrical generator to avoid shutdown of the emergency electrical generator.

6. The emergency power system of claim 1, wherein the mechanical power source is a ram air turbine.

7. The emergency power system of claim 1, wherein the plurality of electrical loads comprise a pilot display, a co-pilot display, an internal navigation computer, a display control unit computer, a transponder, a backup transponder, an air data computer, an air speed data sensor, an air speed pitot tube heater, and a flight control computer.

8. The emergency power system of claim 1, and further comprising:

a hydraulic pump coupling the emergency electrical generator to the mechanical power source;

a plurality of hydraulic loads; and

a hydraulic power distribution network connecting the hydraulic pump to the plurality of hydraulic loads, wherein the controller controls the hydraulic power distribution network to selectively couple and decouple the hydraulic loads to and from the hydraulic pump based upon a priority rank assigned to each of the hydraulic loads.

9. The emergency power system of claim 8, wherein the emergency electrical generator is a motor-generator.

10. The emergency power system of claim 8, wherein the plurality of hydraulic loads comprise a horizontal stabilizer, a vertical stabilizer, a flap, a slat, and an aileron.

11. The emergency power system of claim 1, and further comprising:

current sensors for sensing current supplied by the emergency electrical generator and for sensing current drawn by each of the plurality of electrical loads.

12. The emergency power system of claim 11, wherein the controller predicts the electrical power distribution network demanding emergency power in excess of available emergency power based upon current signals from the current sensors.

13. The emergency power system of claim 11, wherein the controller determines whether to couple and decouple each of the electrical loads to and from the emergency electrical generator based upon current signals from the current sensors as well as the priority rank assigned to each of the electrical loads.

14. A method for managing an emergency power system on an aircraft, the method comprising:

generating emergency electrical power via an emergency electrical generator coupled to a mechanical power source;

distributing the emergency electrical power to a plurality of electrical loads; and

automatically decoupling one or more of the electrical loads from the emergency electrical generator in anticipation of the plurality of loads demanding emergency electrical power in excess of available emergency electrical power, wherein the electrical loads are decoupled based upon a priority rank assigned to each of the electrical loads.

15. The method of claim 14, and further comprising:

determining an expected energy production plan over an anticipated duration of an emergency; and

determining available emergency electrical power based on the expected energy production plan.

16. The method of claim 14, wherein available emergency electrical power includes power available from the mechanical power source, power available from another mechanical power source, and power available from a battery.

17. The method of claim 14, and further comprising:

automatically re-coupling one or more of the electrical loads to the emergency electrical generator in response to an increase in the available emergency electrical power, wherein the electrical loads are re-coupled based upon the priority rank assigned to each of the electrical loads.

18. The method of claim 14, and further comprising:

assigning a reduced priority rank to a failed load in response to determining failure of the failed load.

19. The method of claim 14, and further comprising:

assigning a relatively lower priority rank to a first of two redundant loads; and

assigning a relatively higher priority rank to a second of the two redundant loads.

20. The method of claim 14, wherein the one or more electrical loads are decoupled from the emergency electrical generator in response to a controller determining that the mechanical power source is anticipated to stall absent the one or more electrical loads being decoupled.