DAMAGE ADAPTIVE CONTROL

• US 20140244075A1
• Filed: 02/28/2013
• Published: 08/28/2014
• Est. Priority Date: 02/28/2013
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Litwinowicz, Anthony, Sahasrabudhe, Vineet, Bates, Preston R., Garhart, Jonathan K.
• Granted Patent: US 9,132,911 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 19/00 Aircraft control not otherwise provided for
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G05D 1/0055 with safety arrangements
• CPC Class Codes: G05D 1/0066 for limitation of acceleration or stress

Abstract

Embodiments of the disclosure are directed to measuring, via at least one sensor, at least one of a damage and a compromise associated with a vehicle, determining at least one of a region and a location of the at least one of a damage and a compromise and a level of the at least one of a damage and a compromise, and adapting an operational envelope for the vehicle based on the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise.

Claims

1. A method comprising:

measuring, via at least one sensor, at least one of a damage and a compromise associated with a vehicle;

determining at least one of a region and a location of the at least one of a damage and a compromise and a level of the at least one of a damage and a compromise; and

adapting an operational envelope for the vehicle based on the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise.

2. The method of claim 1, wherein the at least one sensor is mounted on the vehicle.

3. The method of claim 1, wherein the vehicle comprises an aircraft, and wherein the operational envelope is adapted for the aircraft during a flight.

4. The method of claim 3, further comprising:

indicating that the aircraft should be landed based on the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise.

5. The method of claim 1, further comprising:

providing an indication of the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise.

6. The method of claim 1, wherein the at least one of a damage and a compromise applies to a component of the vehicle, and wherein adapting the operational envelope comprises reducing a load imposed on the structure of the vehicle in order to prevent the at least one of a damage and a compromise from propagating through the vehicle structure.

7. An apparatus comprising:

at least one processor; and

memory having instructions stored thereon that, when executed by the at least one processor, cause the apparatus to;

measure at least one of a damage and a compromise associated with a vehicle, determine at least one of a region and a location of the at least one of a damage and a compromise and a level of the at least one of a damage and a compromise, and adapt an operational envelope for the vehicle based on the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise.

8. The apparatus of claim 7, wherein the vehicle comprises an aircraft, and wherein the instructions, when executed by the at least one processor, cause the apparatus to:

measure the at least one of a damage and a compromise to the aircraft structure during a flight, and

adapt the operational envelope for the aircraft during the flight.

9. The apparatus of claim 8, wherein the instructions, when executed by the at least one processor, cause the apparatus to:

provide an indication that the aircraft should be landed based on the determined at least one of a region and a location of the damage and the level of the at least one of a damage and a compromise.

10. The apparatus of claim 7, wherein the instructions, when executed by the at least one processor, cause the apparatus to:

provide an indication of at least one of the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise.

11. The apparatus of claim 7, wherein the vehicle comprises an aircraft, and wherein the at least one of a damage and a compromise applies to a component of the aircraft, and wherein the operational envelope is adapted to reduce a load imposed on the component of the aircraft structure in order to allow for continued safe flight.

12. A system comprising:

at least one sensor configured to provide data associated with an operation of an vehicle; and

a control computer configured to receive the data and analyze the data to determine that a component associated with the vehicle structure is at least one of damaged and compromised;

wherein the control computer is configured to adapt an operational envelope for the vehicle based on the determination.

13. The system of claim 12, wherein the vehicle comprises an aircraft that adheres to a fly-by-wire (FBW) configuration.

14. The system of claim 12, wherein the vehicle comprises an aircraft, and wherein the control computer is configured to determine that the component is at least one of damaged and compromised when the aircraft is on the ground, and wherein the control computer is configured to adapt the operational envelope for the aircraft such that the aircraft remains on the ground until an indication is received by the control computer that a maintenance activity has been performed.

15. The system of claim 12, wherein the vehicle comprises an aircraft, and wherein the control computer is configured to determine that the component is damaged when the aircraft is on the ground, and wherein the control computer is configured to adapt the operational envelope for the aircraft such that the aircraft is configured to fly a reduced mission before the damage is repaired.

16. The system of claim 12, wherein the vehicle comprises an aircraft, and wherein the control computer is configured to determine that the aircraft structure is at least one of damaged and compromised when the aircraft is in flight, and wherein the control computer is configured to adapt the operational envelope based on a determined level of at least one of damage and compromise associated with the component.

17. The system of claim 12, wherein the vehicle comprises an aircraft, and wherein the control computer is configured to receive at least one command based on an actuation of a device located in a cockpit of the aircraft.

18. The system of claim 17, wherein the control computer is configured to limit the at least one command at least to an extent that the at least one command directs an operation of the aircraft that exceeds the operational envelope.

19. A vehicle comprising:

a structure;

at least one sensor configured to generate data pertaining to the structure;

a computing system configured to receive the data, process the data, and generate a control output; and

a propulsion and control surface configured to compensate for an inoperability in the structure based on the control output.

20. The vehicle of claim 19, wherein the vehicle comprises an aircraft, and wherein the computing system is configured to identify a region in the structure where at least one of damage and compromise to the structure has occurred, and wherein the control output is configured to cause the propulsion and control surface to compensate for the at least one of damage and compromise during flight.