# US 2017/0283085 A1 · On-board structural load assessment of an aircraft during flight events

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- Number: US 2017/0283085 A1
- Document ID: US20170283085A1
- Status: Published application
- Kind: A1
- Application number: 15/090,326
- Filed: 2016-04-04
- Published: 2017-10-05
- Earliest claimed: 2016-04-04
- Assignees: The Boeing Company
- Applicants: The Boeing Company
- Inventors: Justin D. Kearns; Rongsheng Li; Naveed Hussain; Kayode T. Ariwodola; Christopher L. Davis; Jack S. Hagelin; Lawrence E. Pado
- Web page: https://patentgrep.com/patent/US20170283085A1

## CPC

- B64D 45/00: Aircraft indicators or protectors not otherwise provided for
- B64F 5/60: Testing or inspecting aircraft components or systems
- G06Q 10/06: Resources, workflows, human or project management; Enterprise or organisation planning; Enterprise or organisation modelling
- G06Q 50/40: Business processes related to the transportation industry (shipping G06Q10/083)
- B64D 2045/008: {Devices for detecting or indicating hard landing}
- B64D 2045/0085: {Devices for aircraft health monitoring, e.g. monitoring flutter or vibration}
- Y02E 10/50: Photovoltaic [PV] energy
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- G06Q: INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES; SYSTEMS OR METHODS SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES, NOT OTHERWISE PROVIDED FOR
- Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION

## Abstract

A system is provided for structural load assessment of an aircraft. An approximator may receive parameters related to a ground or flight event and calculate the resulting response load on the aircraft using a machine learning algorithm and a structural dynamics model of the aircraft. An analysis engine may compare the calculated response load to a corresponding design load for determining the structural severity of the ground or flight event on the aircraft. A maintenance engine may then automatically perform or trigger a maintenance activity for the aircraft in instances in which the structural severity of the ground or flight event causes a limit exceedance state of the aircraft or at least one structural element thereof.

## Claims

### Claim 1

An apparatus for structural load assessment of an aircraft, the apparatus comprising a processor and a memory storing executable instructions that, in response to execution by the processor, cause the apparatus to implement at least:
an approximator configured to receive flight parameters related to at least one of a ground or flight event of the aircraft, and calculate a response load on the aircraft as a result of the at least one ground or flight event, the response load being calculated from the flight parameters and using a machine learning algorithm and a structural dynamics model of the aircraft;
an analysis engine coupled to the approximator and configured to compare the response load to a corresponding design load, and based at least in part on the comparison, determine structural severity of the at least one ground or flight event on the aircraft; and
a maintenance engine coupled to the analysis engine and configured to automatically initiate a maintenance activity requirement for the aircraft in an instance in which the structural severity of the at least one ground or flight event causes a limit exceedance state of at least one of the aircraft or at least one structural element of the aircraft.

### Claim 2 (depends on 1)

The apparatus of claim 1, wherein the approximator being configured to calculate the response load includes being configured to calculate the response load using the machine learning algorithm comprising at least one of a Kalman filter algorithm or a heuristic algorithm, and in at least one instance update at least one of the machine learning algorithm or the structural dynamics model based at least in part on at least one of flight test data or flight operation data.

### Claim 3 (depends on 1)

The apparatus of claim 1, wherein the approximator being configured to calculate the response load includes being configured to calculate the response load using the machine learning algorithm that is or includes a heuristic algorithm, and the heuristic algorithm is or includes at least one of an artificial neural network, Gaussian process, regression, support vector transform, classification, clustering, or principal component analysis algorithm.

### Claim 4 (depends on 1)

The apparatus of claim 1, wherein the approximator being configured to receive the flight parameters includes being configured to receive the flight parameters including at least one of a vertical sink rate, pitch altitude, roll angle, roll rate, drift angle, initial sink acceleration, gross weight, center of gravity, control surface deflections, maximum vertical acceleration at or near at least one of a nose of the aircraft or a pilot seat, maximum longitudinal, lateral, and vertical acceleration at the center of gravity, airspeed, or ground speed of the aircraft.

### Claim 5 (depends on 1)

The apparatus of claim 1, wherein in the instance in which the structural severity of the at least one ground or flight event causes the limit exceedance state of at least one of the aircraft or the at least one structural element of the aircraft, the at least one ground or flight event includes at least one of a hard landing, overweight landing, hard braking event, encounter with turbulence, extreme maneuvering, speed limit exceedance, or stall buffet condition(s) of the aircraft.

### Claim 6 (depends on 1)

The apparatus of claim 1 further comprising a communication interface coupled to the processor and configured to transmit information indicating the structural severity of the at least one ground or flight event to at least one of an external inspection system or a health monitoring system onboard the aircraft, the external inspection system and health monitoring system being configured to download the information thereto.

### Claim 7 (depends on 1)

The apparatus of claim 1 further comprising an input interface coupled to the processor, coupled or coupleable to a control unit of a health monitoring system onboard the aircraft, and through which the approximator is configured to receive the flight parameters from the control unit.

### Claim 8 (depends on 1)

The apparatus of claim 1, wherein at least the processor or the memory are embedded in at least one of a health monitoring system onboard the aircraft, an external inspection system, database, or a portable electronic device.

### Claim 9

A method for structural load assessment of an aircraft, the method comprising:
receiving flight parameters related to at least one of a ground or flight event of the aircraft, and calculating a response load on the aircraft as a result of the at least one ground or flight event, the response load being calculated from the flight parameters and using a machine learning algorithm and a structural dynamics model of the aircraft;
comparing the response load to a corresponding design load, and based at least in part on the comparison, determining a structural severity of the at least one ground or flight event on the aircraft; and
automatically initiating a maintenance activity requirement for the aircraft in an instance in which the structural severity of the at least one ground or flight event causes a limit exceedance state of at least one of the aircraft or at least one structural element of the aircraft.

### Claim 10 (depends on 9)

The method of claim 9, wherein calculating the response load includes calculating the response load using the machine learning algorithm comprising at least one of a Kalman filter algorithm or a heuristic algorithm, and in at least one instance updating at least one of the machine learning algorithm or the structural dynamics model based at least in part on at least one of flight test data or flight operation data.

### Claim 11 (depends on 9)

The method of claim 9, wherein calculating the response load includes calculating the response load using the machine learning algorithm that is or includes a heuristic algorithm, and the heuristic algorithm is or includes at least one of an artificial neural network, Gaussian process, regression, support vector transform, classification, clustering, or principal component analysis algorithm.

### Claim 12 (depends on 9)

The method of claim 9, wherein receiving the flight parameters includes receiving the flight parameters including at least one of a vertical sink rate, pitch altitude, roll angle, roll rate, drift angle, initial sink acceleration, gross weight, center of gravity, control surface deflections, maximum vertical acceleration at or near at least one of a nose of the aircraft or a pilot seat, maximum longitudinal, lateral, and vertical acceleration at the center of gravity, airspeed, or ground speed of the aircraft.

### Claim 13 (depends on 9)

The method of claim 9, wherein in the instance in which the structural severity of the at least one ground or flight event causes the limit exceedance state of at least one of the aircraft or the at least one structural element thereof, the at least one ground or flight event includes at least one of a hard landing, overweight landing, hard braking event, encounter with turbulence, extreme maneuvering, speed limit exceedance, or stall buffet condition(s) of the aircraft.

### Claim 14 (depends on 9)

The method of claim 9 further comprising transmitting information indicating the structural severity of the at least one ground or flight event to at least one of an external inspection system or a health monitoring system onboard the aircraft, the external inspection system and health monitoring system being configured to download the information thereto.

### Claim 15 (depends on 9)

The method of claim 9, wherein receiving the flight parameters includes receiving the flight parameters from a control unit of a health monitoring system onboard the aircraft.

### Claim 16

A computer-readable storage medium for structural load assessment of an aircraft, the computer-readable storage medium having computer-readable program code stored therein that, in response to execution by a processor, cause an apparatus to at least:
receive flight parameters related to at least one of a ground or flight event of an aircraft, and calculate a response load on the aircraft as a result of the at least one ground or flight event, the response load being calculated from the flight parameters and using a machine learning algorithm and a structural dynamics model of the aircraft;
compare the response load to a corresponding design load, and based at least in part on the comparison, determine a structural severity of the at least one ground or flight event on the aircraft; and
automatically initiate a maintenance activity requirement for the aircraft in an instance in which the structural severity of the at least one ground or flight event causes a limit exceedance state of at least one of the aircraft or at least one structural element of the aircraft.

### Claim 17 (depends on 16)

The computer readable storage medium of claim 16, wherein the apparatus being caused to calculate the response load includes being caused to calculate the response load using the machine learning algorithm comprising at least one of a Kalman filter algorithm or a heuristic algorithm, and in at least one instance update at least one of the machine learning algorithm or the structural dynamics model based at least in part on at least one of flight test data or flight operation data.

### Claim 18 (depends on 16)

The computer readable storage medium of claim 16, wherein the apparatus being caused to calculate the response load includes being caused to calculate the response load using the machine learning algorithm that is or includes a heuristic algorithm, and the heuristic algorithm is or includes at least one of an artificial neural network, Gaussian process, regression, support vector transform, classification, clustering, or principal component analysis algorithm.

### Claim 19 (depends on 16)

The computer readable storage medium of claim 16, wherein the apparatus being caused to receive the flight parameters includes being caused to receive the flight parameters including at least one of a vertical sink rate, pitch altitude, roll angle, roll rate, drift angle, initial sink acceleration, gross weight, center of gravity, control surface deflections, maximum vertical acceleration at or near at least one of a nose of the aircraft or a pilot seat, maximum longitudinal, lateral, and vertical acceleration at the center of gravity, airspeed, or ground speed of the aircraft.

### Claim 20 (depends on 16)

The computer readable storage medium of claim 16, wherein in the instance in which the structural severity of the at least one ground or flight event causes the limit exceedance state of at least one of the aircraft or the at least one structural element thereof, the at least one ground or flight event includes at least one of a hard landing, overweight landing, hard braking event, encounter with turbulence, extreme maneuvering, speed limit exceedance, or stall buffet condition(s) of the aircraft.

### Claim 21 (depends on 16)

The computer readable storage medium of claim 16 having further computer-readable program code portions stored therein that in response to execution by the processor, cause the apparatus to at least transmit information indicating the structural severity of the at least one ground or flight event to at least one of an external inspection system or a health monitoring system onboard the aircraft, the external inspection system and health monitoring system being configured to download the information thereto.

### Claim 22 (depends on 16)

The computer readable storage medium of claim 16, wherein the apparatus being caused to receive the flight parameters include being caused to receive the flight parameters from a control unit of a health monitoring system onboard the aircraft, and in at least one instance, transmitting information indicating the structural severity of the at least one ground or flight event on the aircraft to the health monitoring system, the health monitoring system being configured to download the information thereto.