Determining a load condition of an aircraft
Disclosed are methods and devices for determining a load condition of an aircraft. A sensing device is mountable relative to an aircraft strut during loading operations and demountable after loading operations. A data processing device is operable to process output from the sensing device together with aircraft specific data, to determine a load condition of the aircraft.
1 . A sensing device, comprising:
a sensor operable to sense a characteristic related to a length of a strut of a landing gear of an aircraft, the device being mountable relative to the strut during loading operations and demountable after loading operations prior to the aircraft moving from the loading operations position,
the sensing device being operable to provide an output relating to the sensed characteristic for receipt by a data processing device operable to use the received output to determine a load condition of the aircraft during loading operations,
wherein the sensor is operable to sense an angle between first and second link arms of a link mechanism of the landing gear about a common pivot axis, the sensing device comprising first and second pivotally interconnected members, respective mount portions of the members being adapted to be removably mountable to the link mechanism so as to align a pivot axis of the sensing device with the common pivot axis of the first and second arms, and
wherein the sensing device further comprises first and second members pivotally interconnected at end portions thereof, wherein respective opposite end portions of the members comprise respective quick release mount portions for removably mounting the members directly to respective link arms of the link mechanism.
2 . A sensing device according to claim 1 , comprising a further sensor for sensing temperature at or adjacent the strut, the sensing device operable to provide a further output relating to the sensed temperature for receipt by the data processing device.
3 . A sensing device according to claim 1 , further comprising a processor and a memory, the processor being in communication with the or each sensor and the memory, the processor being operable to receive data from the or each sensor and to store the received data in the memory.
4 . A sensing device according to claim 1 , further comprising a communications interface for communicating sensed output to the data processing device, the communications interface comprising a wireless data interface.
5 . A sensing device according to claim 1 , operable to sense a longitudinal distance between a first location fixed for movement relative to a strut cylinder and a second location fixed for movement relative to a strut piston.
6 . A sensing device according to claim 1 , further comprising at least one of a rotary transducer, linear transducer, optical sensor.
7 . A sensing device, comprising: a sensor operable to sense a characteristic related to a length of a strut of a landing gear of an aircraft, the device being mountable relative to the strut during loading operations and demountable after loading operations prior to the aircraft moving from the loading operations position, the sensing device being operable to provide an output relating to the sensed characteristic for receipt by a data processing device operable to use the received output to determine a load condition of the aircraft during loading operations, wherein the sensor is operable to sense an angle between i) a first and/or second link arm of a link mechanism of the landing gear and ii) a longitudinal axis of the strut, the sensing device comprising first and second pivotally interconnected members, respective mount portions of the members being adapted to be removably mountable respectively to i) the first or second link arm and ii) to the strut, so as to align a pivot axis of the sensing device with a pivot axis of the first or second link arm.
8 . A sensing device according to claim 7 , the sensing device comprising first and second members pivotally interconnected at end portions thereof, wherein respective opposite end portions of the members comprise respective quick release mount portions for removably mounting the members respectively i) to the first or second link arm and ii) relative to a cylinder or piston of the strut.
9 . A data processing device comprising a processor and a memory, the device operable to:
receive output relating to the length of a strut of at least one aircraft landing gear from at least one respective sensing device according to claim 1 .
10 . A data processing device according to claim 9 , operable to receive further output relating to a further sensed attribute of the or each strut, the attribute having a functional relationship with strut length, and to process the further output in determining the load condition of the aircraft.
11 . A data processing device according to claim 9 , wherein the further sensed attribute comprises temperature at or adjacent the or each strut, and the data processing device is operable to access an aircraft specific look up table or function to estimate a value for the load on the or each respective landing gear based on values relating to temperature and strut length.
12 . A data processing device according to claim 9 , operable to compute a value for at least one of the following load conditions:
a. a load on the or each landing gear;
b. a total weight on wheels of the aircraft;
c. a position of a centre of gravity of the aircraft;
d. a speed and direction of travel of a centre of gravity of the aircraft; and
e. a rate of change of speed and direction of travel of a centre of gravity of the aircraft.
13 . A data processing device according to claim 12 , operable to compare at least one computed load condition value with a respective aircraft specific critical load condition value and to generate an alert signal if the comparison indicates an adverse condition.
14 . A data processing device according to claim 13 , wherein the alert signal comprises at least one of the following:
a. a signal for receipt by a display of the data processing device, or a remote display, to cause the display of a visual warning;
b. a signal for receipt by an audio system of the data processing device, or a remote audio system, to cause an audible warning;
c. a signal for receipt by a cargo loading system, to instruct an operator or machine to stop or reverse loading operations; and
d. a signal for receipt by an on aircraft system accessible to flight crew, to provide visible or audible advice of the adverse condition.
15 . A method of determining a load condition of an aircraft in a loading operations position of a ground loading operations area comprising:
a. mounting the sensing device according to claim 1 relative to the strut of the aircraft landing gear;
b. using a processor to process output from the sensing device relating to strut length to provide a strut length related value;
c. using a processor to process aircraft specific data and/or further data relating to a further sensed attribute of the landing gear, together with the strut length related value, to provide a value for load on the landing gear; and
d. demounting the sensor prior to the aircraft moving from the loading operations position.
16 . A method according to claim 15 , wherein the further sensed attribute comprises temperature at or adjacent the strut, and the processor uses an aircraft specific look up table or function to determine a value for load on the landing gear based on computed values of temperature and strut length.
17 . A method according to claim 15 , further comprising computing a value for at least one selected from the following load conditions:
a. a load on a landing gear;
b. respective loads on a plurality of respective landing gears each having a respective sensing device mounted thereto;
c. a total weight on wheels of the aircraft;
d. a position of a centre of gravity of the aircraft;
e. a speed and direction of travel of a centre of gravity of the aircraft; and
f. a rate of change of speed and direction of travel of a centre of gravity of the aircraft.
18 . A method according to claim 17 , further comprising comparing at least one computed load condition value with a respective aircraft specific critical load condition value and to generate an alert signal if the comparison indicates an adverse condition.