An Efficient Analysis Method for Prediction and Structural Dimensioning of Wing-Pylon-Adapter-Rocket Pod Assembly Subjected to Shock Loading Hindustan Aeronautics Limited

Format:

Conference/Event

Author/Creator:

Suresh, Suresh, author.

Contributor:

Acharya, Udupi Ananthakrishna

Dhande, Rajkumar

Conference Name:

SAE 2016 Aerospace Systems and Technology Conference (2016-09-27 : Hartford, Connecticut, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2016

Summary:

AbstractReducing the amount of physical testing is of importance in the aeronautical industry, where each physical test represents a significant cost. Apart from the cost aspect, it may also be difficult or hazardous to carry out physical testing. Specific to the aeronautic industry are also the relatively long development cycles, implying long periods of uncertainty during product development. In any industry a common viewpoint is that of verification, validation, and uncertainty quantification using simulation models are critical activities for a successful development of a product.In Aeronautical application, the design of store's structural equipments needs to be certified in accordance with MIL-T-7743F [1]. This paper focuses on a case study for shock analysis, whereby an attempt has been made to reduce the cost of certification by way of replacing the actual physical testing by a reliable high fidelity FE simulation. According to the certification standard the design of external stores carriage need to show compliance either by a full-fledged specified shock and vibration testing or by an equivalent analysis. The overall outcome of the simulation method proves its reliability in the structural integration for the applied shock load as a replacement for actual shock tests

Notes:

Vendor supplied data

Publisher Number:

2016-01-2047

Access Restriction:

Restricted for use by site license