Aircraft weight and center of gravity indicator

Details Aircraft weight and center of gravity indicator Aircraft weight and center of gravity indicator

G - Physics

01

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G01G 19/07 (2006.01) G01L 19/04 (2006.01) G01M 1/12 (2006.01)

Patent

CA 2129521

An onboard system for use in measuring, computing and dis- playing the gross weight and location/relocation of the center of gravi- ty, for aircraft (1). Temperature and pressure transmitters aced transdu- cers (49; 53) are mounted in relation to each of the landing gear struts (8). Transmit those temperature and pressure signals to an onboard micro-computer/controller with redundancy for accuracy and failure protection: The system also incorporates a software lion program to correct and compensate for, physical changes to strut components due to temperature fluctuations, O-ring seal (11) drag and hysteresis within modern day "shock absorbing'. aircraft landing Bear struts. The computer makes adjustments for internal temperature changes and drag, converts sustained pressures to the weight supported by each strut, and computes the aircraft's current gross weight aced center of gravity: The computer also is pre-programmed to illuminate a "Hard Landing Indicator Light" mounted on the display (29), when pre-pro- grammed individual strut pressure limits are exceeded and sensed dur- ing landing. These pressure readings are stored in the computer memo- ry and can be utilized when the aircraft is inspected and serviced.

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