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Development of a μPPT for CubeSat applications

Pottinger, SJ, Krejci, D and Scharlemann, CA (2008) Development of a μPPT for CubeSat applications In: 44th AIAA/ASME/SAE/ASEE 2008: Propulsion Technologies for Next-generation System Solutions, 2008-07-21 - 2008-07-23, Hartford, USA.

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An analytical model based on an oscillatory circuit equation and dynamic equation for a uniform plasma slug has been developed in order to provide a design tool which is able to predict the dependence of µPPT performance on electrode configuration and circuit paramters. The results of the model show good aggrement with experimental results and have been implemented to improve µPPT performance. Thruster performance has been experimentally characterised for a capacitance range of 2 to 31 µF and propellant surface areas of 0.25 to 1.5 cm2 for low energy operation. Results indicate that the impulse bits required for picosatellite missions are achievable with the application of miniaturised thruster heads and energy densities of approximatley 5 to 10 Jcm2.

Item Type: Conference or Workshop Item (UNSPECIFIED)
Divisions : Surrey research (other units)
Authors :
Krejci, D
Scharlemann, CA
Date : 2008
Contributors :
publisherAmerican Institute of Aeronautics and Astronautics,
Depositing User : Symplectic Elements
Date Deposited : 17 May 2017 11:55
Last Modified : 23 Jan 2020 17:24

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