Light weight aircraft weighing system

Madhavan, Chinmayee and Rajanna, D and Dasannacharya, BS and Venkataramanappa, IP and Jayachandran, C and Chandrasekar, KN (1987) Light weight aircraft weighing system. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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One important parameter in the calculation of the performance of an aircraft is its weight. There are two methods commonly used for aircraft weighing. In one method, platform is used under each tier. In this method four load cells are located in the four corners of a13; platform and signals of each load cell are brought out through a connector on one side of the platform. Ramps leading up to the platform are used to roll the aircraft on and off the platform. In the second method load cell is placed on a jack under each axle. Aircraft is then jacked13; up off the ground to put its full weight on the load cells. The load cell outputs are processed and the sum of the three processed outputs gives the weight of the aircraft. This document describes an Aircraft Weighing System having a range of 0-1000kg. The system has an accuracy of +0.1% of the full range and a resolution of +10 gms. The system consists of three weighing platforms, each of them incorporating four load cells fitted in a frame work. Two of the platforms have a range of13; 0-300 kg and the third has a range of 0-60 kg. The system was developed for the Flight Research Group of the division, during the fabrication and operation of the Light Canard Research Aircraft (LCRA). The front wheel of the aircraft is placed on the platform with the range and platforms with larger ranges are used for the two rear wheels.

Item Type: Monograph (Technical Report)
Uncontrolled Keywords: Strain gauge;Load cell weighing;Aircraft weighing;13; Electronic weighing
Subjects: AERONAUTICS > Avionics & Aircraft Instrumentation
Depositing User: Mr. Ravikumar R
Date Deposited: 14 Sep 2006
Last Modified: 24 May 2010 04:20

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