Sheshadri, TS (2000) Anode surface temperature profile in MPD thrusters. In: VACCUM, 54 (09). pp. 904-909.
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A mathematical formulation of the magnetoplasmadynamic (MPD) thruster internal flow problem developed earlier is linked to constraints imposed by an external electrical power supply by the use of an energy equation and an integral energy condition applied over the thruster volume. The formulation is used to obtain anode surface temperature profiles as a function of electrical input power for three different propellants. The results indicate that if the input power is too little or too much the thruster does not perform as an efficient electromagnetic accelerator and the anode surface heats up resulting in erosion and thruster destruction. In the range of parameters studied, argon propellant gave the best performance with a specific impulse of 2000 s, at a mass flow rate of 565 mgm/s and a power input of 3 kW. This makes the argon MPD thruster an ideal choice for use on INSAT class satellites for orbit transfer and station keeping.
|Item Type:||Journal Article|
|Additional Information:||Copy right belongs to Elsevier|
|Keywords:||Materials Science;Multidisciplinary;Physics, Applied|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||04 Dec 2008 06:02|
|Last Modified:||19 Sep 2010 04:52|
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