Slung load identification with aircraft flight dynamics data

• US 10,266,279 B2
• Filed: 09/14/2015
• Issued: 04/23/2019
• Est. Priority Date: 09/19/2014
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Sane, Harshad S., Connor, Michael Aaron, Cherepinsky, Igor
• Primary Examiner(s): Marc-Coleman, Marthe Y
• Application Number:
  US15/509,921
• Publication Number:
  US 20180229855A1
• Time in Patent Office: 1,317 Days
• Field of Search: 701 3
• CPC Class Codes: B64C 27/04 Helicopters
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G05B 17/02 electric

Abstract

A system and method for identifying a slung load for an aircraft with one or more sensors includes receiving, with a processor via one or more sensors, sensor information related to flight dynamics data for the aircraft; determining, with the processor, control input commands for the aircraft in response to the receiving of the flight dynamics data; determining, with the processor, signals indicative of an estimated pendulum frequency; and determining, with the processor, parameters associated with the slung load in response to the determining of the estimated pendulum frequencies.

Claims

1. A method for identifying a slung load for an aircraft, comprising:

receiving, with a processor via one or more sensors, sensor information related to flight dynamics data for the aircraft;

determining, with the processor, control input commands for the aircraft in response to the receiving of the flight dynamics data;

determining, with the processor, an estimated pendulum frequency of the slung load from the control input commands; and

determining, with the processor, a change in the slung load from the estimated pendulum frequencies.

2. The method of claim 1, wherein the receiving of the sensor information further comprises receiving the flight dynamics data related to at least one of load rigid body modes, sling stretching, and load aerodynamics.

3. The method of claim 1, wherein the determining of the estimated pendulum frequency further comprises determining a longitudinal pendulum frequency or a lateral pendulum frequency.

4. The method of claim 1, further comprising determining the estimated pendulum frequency through an online system identification model that includes estimated values of longitudinal and lateral pendulum frequencies, wherein a configuration of the slung load is used to choose the online system identification model.

5. The method of claim 1, wherein the determining of the control input commands further comprises determining commands associated with pitch and roll of the aircraft.

6. The method of claim 1, wherein the determining of the parameters further comprises storing a history of flight dynamics data for the aircraft.

7. The method of claim 6, wherein the determining of the parameters further comprises determining a difference in the estimated pendulum frequency from a first time period to a second time period, the second time period being later than the first time period.

8. The method of claim 6, wherein the determining of the parameters further comprises determining whether a difference in the estimated pendulum frequency from a first time period to a second time period is above a threshold value, the second time period being later than the first time period, to determine a change in a mass of the slung load.

9. A system for identifying a slung load for an aircraft, comprising:

one or more sensors coupled to the aircraft;

a load sling assembly including a sling coupled to an attachment device and a cargo;

memory having instructions stored thereon that, when executed by the processor, cause the system to;

receive sensor information related to flight dynamics data for the aircraft;

determine control input commands for the aircraft in response to the receiving of the flight dynamics data;

determine an estimated pendulum frequency of the slung load from the control input commands; and

determine a change in the slung load from the estimated pendulum frequencies.

10. The system of claim 9, wherein the processor is configured to receive the flight dynamics data related to at least one of load rigid body modes, sling stretching, and load aerodynamics.

11. The system of claim 9, wherein the processor is configured to determine a longitudinal pendulum frequency or a lateral pendulum frequency.

12. The system of claim 9, wherein the processor is configured to determine the estimated pendulum frequency through an online system identification model that includes estimated values of longitudinal and lateral pendulum frequencies, wherein a configuration of the slung load is used to choose the online system identification model.

13. The system of claim 9, wherein the processor is configured to determine commands associated with pitch and roll of the aircraft.

14. The system of claim 9, wherein the memory is configured to store a history of flight dynamics data for the aircraft.

15. The system of claim 14, wherein the processor is configured to determine whether a difference in the estimated pendulum frequency from a first time period to a second time period is above a threshold value, the second time period being later than the first time period, to determine a change in a mass of the slung loads.