An aircraft landing gear assembly 112 comprises a shock absorber strut 114, a bogie 120, a link assembly 124, and a movement detector 132. The shock absorber strut 114 comprises upper and a lower telescoping parts 118, 116, the lower part 116 being connected to the bogie 120 which may adopt different pitch angles. The link assembly 124 extends between the upper and lower telescoping parts 118, 116, such that relative movement between the upper and lower telescoping parts 118, 116 causes relative movement between parts of the link assembly 124. The movement detector 132 detects movement of the link assembly 124 relative to the bogie 120. The movement detector 132 may comprise: a piston 138 slidably received within a cylinder 136, fluid which flows as a result of relative movement between the piston 138 and the cylinder 136 and a flow sensor 184 arranged to sense a change in flow of the fluid in a conduit 180. The present invention also provides a method of detecting aircraft weight on wheels. The sensor may be a hot wire transducer 84, a hot film transducer (384 fig. 8), one or more pressure transducers (484 fig. 9, 584, 585, 586 fig. 10) or ultrasonic transducers (684 fig. 11) measuring fluid flow velocity.


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    Titel :

    Aircraft landing gear assembly


    Beteiligte:

    Erscheinungsdatum :

    02.01.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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