Aircraft weighing system

Madhavan, Chinmayee and Dasannacharya, BS and Rajanna, D and Nagabhushana, S (1985) Aircraft weighing system. Technical Report. National Aeronautical Laboratory, Bangalore, India.

Full text available as:
[img] PDF
Restricted to Archive staff only

Download (312Kb)

    Abstract

    The memorandum describes an Aircraft Weighing System13; developed for weighing an aircraft to determine its gross weight and centre of gravity (CG). As the stability of an aircraft depends on the CG-AC relationship, its gross weight and center of gravity should be kept within the designed specifications. Deviations from this, results in poor performance and possible catastrophic instability. Hence an accurate Aircraft Weighing System is required for the development and testing of an aircraft. The system is designed for a range of 30 tonnes,calibrated to an accuracy of +/- 0.1 % of the range with a resolution of +/- 0.03% of the range.Longitudinal position of Centre of Gravity is calculated from the measured gross weights and perpendicular distance between the nose wheel and the main wheels. Vertical position of the center of gravity relative to a reference datum can be determined using horizontal position of the CG and weight of the aircraft. Transverse position of the CG is usually maintained on the transverse axis itself by symmetry during fabrication.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Electronic weighing;CG determination;Aircraft weighing
    Subjects: AERONAUTICS > Aircraft Stability and Control
    AERONAUTICS > Aircraft Design, Testing & Performance
    Division/Department: Systems Engineering Division, Systems Engineering Division, Systems Engineering Division, Systems Engineering Division
    Depositing User: M/S ICAST NAL
    Date Deposited: 28 Nov 2006
    Last Modified: 24 May 2010 09:53
    URI: http://nal-ir.nal.res.in/id/eprint/3528

    Actions (login required)

    View Item