Aircraft Emergency Handling

• US 20090306836A1
• Filed: 10/19/2007
• Published: 12/10/2009
• Est. Priority Date: 12/19/2005
• Status: Active Grant

• Current Assignee: Astronics Advanced Electronic Systems Corporation (Astronics Corporation)
• Original Assignee: Vertical Power, Inc. (Astronics Corporation)
• Inventors: DeVries, Kevin, Ausman, Marc
• Granted Patent: US 8,340,842 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: G01D 2207/10 Displays which are primarily used in aircraft or display aircraft-specific information
• CPC Class Codes: G01D 7/00 Indicating measured values

Abstract

The present invention provides methods and apparatuses that reduce pilot workload and increase the performance and efficiency of the pilot'"'"'s control of the aircraft. The present invention comprises methods and apparatuses for determining the presence and type of an emergency condition, for example by detecting corresponding sensor outputs or by accepting input from a pilot or a combination thereof; and then responding to that emergency by initiating a pre-determined set of actions specific to the determined emergency. Embodiments of the invention can include the ability to monitor engine conditions as well as control electrical functions such as the fuel boost pump, alternator field, battery contactor and other important electrical devices. Some examples described below assume a single-engine piston aircraft for ease of illustration. The invention can also be applied to multi engine and turbine powered aircraft as well.

Claims

1. A method of assisting a pilot in management of an emergency condition in an aircraft, comprising:

a. Accepting an indication of the presence of an emergency condition;

b. Determining a specific emergency condition from a plurality of possible emergency conditions;

c. Automatically controlling a plurality of operating parameters of the aircraft responsive to the specific emergency condition.

2. A method as in claim 1, wherein the possible emergency conditions include one or more of engine failure, engine fire, alternator failure, and electrical fumes.

3. A method as in claim 1, wherein the plurality of operating parameters include one or more of fuel boost, alternator power, electrical system load, engine starter, and bus cross tie contactor.

4. A method as in claim 1, wherein, if the specific emergency condition is an engine failure, then automatically turning on the fuel boost, the engine ignition system, and the alternator, and then activating the engine starter in response to further direction from a pilot.

5. A method as in claim 1, wherein, if the specific emergency condition is an engine fire, then automatically turning off the fuel boost and the alternator;

and turning off additional electrical systems in response to further input from a pilot.

6. A method as in claim 1, wherein, if the specific emergency condition is electrical fumes, then determining weather conditions, and automatically shedding load from the aircraft electrical system, where the specific loads shed are determined in part from the weather conditions, and turning off additional electrical systems in response to further direction from a pilot.

7. A method as in claim 1, wherein, if the specific emergency condition is alternator failure, and the aircraft has a single bus, then automatically turning the primary alternator on, waiting a predetermined time, then determining whether the bus voltage is above a threshold, and if not, then turning off primary alternator, determining weather conditions and shedding loads from the aircraft electrical system, where the specific loads shed are determined in part from the weather conditions, then turning on the backup alternator, if present.

8. A method as in claim 1, wherein, if the specific emergency condition is alternator failure, and the aircraft has a dual bus, then determining whether either bus voltage is below a threshold, and if so, then automatically turning the alternator associated with that bus on, waiting a predetermined time, then determining whether the bus is above a predetermined threshold, and, if not, then turning off alternator on failed bus, determining weather conditions and shedding loads from the bus, where the specific loads shed are determined in part from the weather conditions, and closing the cross tie contactor.

9. A method as in claim 1, further comprising determining if the emergency condition has abated, and, if so, then automatically returning all aircraft operating parameters to their pre-emergency states.

10. A method as in claim 1, further comprising determining if the emergency condition has abated, and, if so, then automatically returning some aircraft operating parameters to their pre-emergency state and leaving other aircraft operating parameters in the state established under automatic control.

11. A method as in claim 1, wherein accepting an indication of the presence of an emergency condition comprises an input from a pilot.

12. A method as in claim 1, wherein accepting an indication of the presence of an emergency condition comprises determining the presence of an emergency condition from a combination of a plurality of sensors.

13. A method as in claim 1, wherein determining the specific emergency condition comprises accepting a pilot input specifying a specific emergency condition.

14. A method as in claim 1, wherein determining the specific emergency condition comprises determining a specific emergency condition from a combination of a plurality of sensors.

15. A system for assisting a pilot of an aircraft in the management of an emergency condition, comprising:

a. An emergency presence element, adapted to determine the presence of an emergency condition from sensor signals, pilot input, or a combination thereof;

b. An emergency determination element, adapted to determine a specific emergency condition from sensor signals, pilot input, or a combination thereof;

c. A response element, adapted to automatically control a plurality of operating parameters responsive to the specific emergency condition.

16. A system as in claim 15, wherein the emergency presence element comprises a switch actuable by a pilot to indicate the presence of an emergency.

17. A system as in claim 15, wherein the emergency determination element comprises a display adapted to communicate to a pilot a plurality of possible emergency conditions, and one or more pilot input mechanisms allowing a pilot to select one of the plurality of possible emergency conditions.

18. A system as in claim 17, wherein at least one of the pilot input mechanisms comprises a soft button controlled in coordination with the display.

19. A system as in claim 15, wherein the emergency presence element is further adapted to determine when the emergency condition is abated.

20. A system as in claim 19, wherein the response element is further adapted to control one or more operating parameters to their pre-emergency state responsive to an indication that the emergency condition is abated.

21. A system as in claim 15, further comprising a display adapted to communicate to a pilot a checklist of actions corresponding to a specific emergency condition.