An on-board aircraft system for determining the weight and load-related characteristics of an aircraft having landing gear struts (which each have a strut cylinder, a strut piston, and a working fluid in the strut cylinder) includes an accelerometer associated with each gear strut for measuring acceleration. The system further includes a pressure-adjustment means coupled to each strut cylinder for selectively adjusting the pressure in each strut cylinder to cause each landing gear strut to extend and retract; a plurality of pressure transducers coupled to the plurality of landing gear struts for measuring a pressure in each strut cylinder; and a computer. The computer is operable to cause retracting and extending the strut, to store pressure measurements of the strut cylinder during the retraction and extension of the strut, to store acceleration measurements corresponding to each pressure measurement taken, and to calculate the weight based on the pressure measurements and the acceleration measurements. A method of determining the weight on an aircraft is disclosed that includes use of an accelerometer.

System and method for on-board determination of aircraft weight and load-related characteristics

An apparatus for determining the weight and/or center of gravity of an aircraft is disclosed and includes a plurality of fittings attached to each oleo strut on the aircraft for accessing the working fluid in the oleo strut, a computer, a first, electronically-responsive valve coupled to each fitting for controlling the fluid flow through the fitting in response to control signals from the computer, a pressure transducer coupled downstream of the first valve for measuring the pressure of the working fluid therein and coupled to the computer to provide a pressure measurement signals to the computer for each strut, and an inclinometer attached to the aircraft and electronically coupled to the computer for providing incline information to the computer. A method is disclosed that includes accessing the working fluid of each oleo strut cylinder, attaching a pump to each oleo strut cylinder, cycling each oleo strut cylinder between a near fully extended position and a near fully retracted position while recording pressure measurements in the cylinder at a plurality of points between the two positions while keeping the aircraft level, and mathematically manipulating the recorded pressure measurements to arrive at an approximation of the weight on each strut. The total weight can be then found by adding the weight on each strut plus any dead weight for each strut. The center of gravity may then be determined by summing the moments for each load on each strut and dividing the total or sum of the moments by the total weight to arrive at the center of gravity.

On-board aircraft weighting and center of gravity determing apparatus and method

An arrangement in which at least one sensor is provided on the landing gear of an aircraft for measuring its weight and the position of its center of gravity, and in which a sensor for a measurement of shear is arranged at a measurement point formed by a pair of lugs on an axle or bogie beam. The axle (9) or bogie beam is of constant cross section above the measurement point and symmetrical to a vertical axis which lies centrally between the two lugs of a pair (10, 13 and 14, 15 respectively).

Arrangement of at least one sensor on the landing gear of an aircraft for measuring its weight and position of center of gravity

A computer apparatus and method to determine aircraft fuel mileage performance. The computer apparatus including a memory and a processor disposed in communication with the memory and configured to issue a plurality of instructions stored in the memory. The instructions issue signals to receive real-time aircraft data during aircraft flight and process the real-time data to determine real-time aircraft mass data. A calculation is performed to determine the real-time fuel mileage performance for the aircraft based upon determined real-time aircraft mass data.

System and method for real-time aircraft performance monitoring

By the fastening device, two electric transmitters are to be arranged on a supporting structural part from which two extensions (11) protrude spaced from each other. For this purpose, one bored attachment end (15, 16) each of the two transmitters are arranged each on one side (13, 14) of one of the two extensions (11) on a threaded bolt (1, 2). The threaded bolt is screwed, with one collar (5, 6) each lying on both sides against the extension (11), directly to the latter. The attachment ends each have such a large recess (20 22) that they rest only on the extension without resting on the collars (5, 6). The threaded bolt (1, 2) is provided on the outside on both ends with a threaded section (9, 10). Nuts (25, 26) which are screwed on the respective threaded sections press in each case one of the two attachment ends (15, 16) against the extension (11).

Fastening device for the attaching of an electric transmitter

A variable reluctance transducer assembly for measuring the strain deflection in a structural member includes an elongate housing which is mounted to a first lug extending transversely outwardly from the structural member. The housing supports a pair of magnetic cores in spaced parallel relationship to each other. Each core in turn supports a wire coil. The coils are wired to each generate a magnetic field when energized by an electric current. The transducer assembly is also composed of an elongate target mounted on a second lug extending transversely from the structural member at a location longitudinally spaced from the other lug. The target includes a plate portion which extends longitudinally toward the housing to lie nominally between the two spaced apart cores and their corresponding coils to form a portion of the path along which the magnetic lines of flux eminating for each of the two coils travels. A flexible metal bellows interconnects the housing and target to enclose the cores and target plate while simultaneously permitting the target plate to move toward and away from the cores in response to the relative movement between the mounting lugs to thereby vary the reluctance between the target plate and each coil.

Strain/deflection sensitive variable reluctance transducer assembly

Variable magnetic resistance converter assembly and correction thereof

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Strain/deflection sensitive variable reluctance transducer assembly

Variable magnetic resistance converter assembly and correction thereof