TY - GEN
T1 - Employing rapid prototyping to reduce weight and optimize selected intricate structural components of a picosatellite
AU - Marne, Aniket
AU - Katke, Tanvi
AU - Kamble, Saranga
AU - Prabhune, Bhagyashree
AU - Kothawala, Ali Murtaza
AU - Rathod, Abhijit
AU - Bobade, Pradip
PY - 2015
Y1 - 2015
N2 - Rapid prototyping creates a 'prototype' of the CAD model at a fast rate, building the object layer by layer, from the bottom to the top. Swayam is a 1U, low earth orbit pico-satellite and weighs 1 kg. Its payload is passive attitude stabilization, i.e. without consuming on-board power. It will be launched as an auxiliary satellite on board ISRO's polar satellite launch vehicle. In the satellite, non-conducting and non-magnetic materials are needed for housing components like magnet, hysteresis rods and switches from inertial and vibrational loads. Considering various factors such as strength, availability, weight and cost, acrylonitrile butadiene styrene (ABS) has been found to be suitable for these components. Tensile and hardness tests have been performed on ABS for verifying its properties. ABS does not interfere with the satellite's attitude control system. Simulations were run to check the stress levels due vibrations. Stress values so obtained were found to be less than allowable stress values. Components having irregular and intricate shapes such as antenna extension, switch cases were manufactured with ease which is not possible or extremely difficult to manufacture by any other means. These components have been designed considering various stresses to which ABS would be subjected. They have been manufactured using the fused deposition modelling (FDM) type of rapid prototyping technique. The paper explains how RPT was employed to optimize the structure and reduce weight.
AB - Rapid prototyping creates a 'prototype' of the CAD model at a fast rate, building the object layer by layer, from the bottom to the top. Swayam is a 1U, low earth orbit pico-satellite and weighs 1 kg. Its payload is passive attitude stabilization, i.e. without consuming on-board power. It will be launched as an auxiliary satellite on board ISRO's polar satellite launch vehicle. In the satellite, non-conducting and non-magnetic materials are needed for housing components like magnet, hysteresis rods and switches from inertial and vibrational loads. Considering various factors such as strength, availability, weight and cost, acrylonitrile butadiene styrene (ABS) has been found to be suitable for these components. Tensile and hardness tests have been performed on ABS for verifying its properties. ABS does not interfere with the satellite's attitude control system. Simulations were run to check the stress levels due vibrations. Stress values so obtained were found to be less than allowable stress values. Components having irregular and intricate shapes such as antenna extension, switch cases were manufactured with ease which is not possible or extremely difficult to manufacture by any other means. These components have been designed considering various stresses to which ABS would be subjected. They have been manufactured using the fused deposition modelling (FDM) type of rapid prototyping technique. The paper explains how RPT was employed to optimize the structure and reduce weight.
UR - http://www.scopus.com/inward/record.url?scp=84994242607&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84994242607
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 6767
EP - 6776
BT - 66th International Astronautical Congress 2015, IAC 2015
PB - International Astronautical Federation, IAF
T2 - 66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015
Y2 - 12 October 2015 through 16 October 2015
ER -