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Aviation batteries are the power source for independent starting of aircraft engines & emergency backup in case of generator failure on board aircraft. These batteries have to be with stand environment effects induced by the aircraft and the environment effects due to high altitudes etc.
In the present study, a typical battery container has been taken as pilot model for the actual battery in order to study the deformation, cracks and induced stresses due to environmental effects (Mechanical shock, Acceleration and Vibration) according to MIL-STD-810E 14th July 18 and JSS 6140 07001.The boundary conditions will be studied and finalized for the environment, Temperature.
Finite Element Method has been used to analysis. The analysis has been carried out in the following five phases.
Ø The effect of the clamping forces Static analysis.
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Ø The effect of the Mechanical shock Static analysis.
Ø Determination of the Natural frequencies and mode shapes Modal analysis.
Ø The effect of the Vibration Harmonic analysis.
Ø The effect of the Acceleration Transient analysis. 1.1 AVIATION BATTERY
Aviation Batteries are the power source for independent starting of aircraft engines & emergency backup in case of generator failure on board aircraft. Since these batteries are airbone, the batteries have to meet other conditions like ability to meet acceleration, vibration, shock, thermal shock (explained in chapter of this theses) etc.
These batteries are tested for airworthiness apart from electrical performance. There are several international standards are available which specify the airworthiness of the product. In India, the batteries must undergo
the tests conducted / specified by 'The Center for Military Airworthiness', 'Ministry of Defense Govt. of India' and 'Directorate General of Civil Aviation.
These tests are simulating the aircraft environment. These are expensive, time consuming and failure at that stage involves start the cycle from starting.
In order to provide tools for analysis at design phase, the batteries are modeled and the airworthiness tests are conducted mathematically, in the design phase, will help in optimizing the design.
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