RITA Ion Propulsion Systems for Commercial and Scientific Applications

2007 ◽  
Author(s):  
Rainer Killinger ◽  
Hans Leiter ◽  
Ralf Kukies
Keyword(s):  
Scientific Applications ◽  
Propulsion Systems ◽  
Ion Propulsion

Ion Propulsion Systems

2008 ◽  
pp. 265-301 ◽  
Author(s):  
H. Bassner ◽  
R. Killinger ◽  
J. Mitterauer ◽  
F. Rüdenauer ◽  
N. Koch ◽  
...  
Keyword(s):  
Propulsion Systems ◽  
Ion Propulsion

scholarly journals Optimizing ideal ion propulsion systems depending on the nature of the propellant

2016 ◽  
Vol 8 (4) ◽  
pp. 93-103 ◽  
Author(s):  
CICAN Grigore ◽  
◽  
POPA Ionut-Florian ◽  
Keyword(s):  
Propulsion Systems ◽  
Ion Propulsion

Ion propulsion systems for spacecraft

1965 ◽  
Vol 2 (4) ◽  
pp. 577-583 ◽  
Author(s):  
PAUL D. READER ◽  
WILLIAM R. MICKELSEN
Keyword(s):  
Propulsion Systems ◽  
Ion Propulsion

Micromachined gas flow regulator for ion propulsion systems

2002 ◽  
Vol 38 (3) ◽  
pp. 982-988 ◽  
Author(s):  
P. Bruschi ◽  
A. Diligenti ◽  
M. Piotto
Keyword(s):  
Gas Flow ◽  
Propulsion Systems ◽  
Ion Propulsion ◽  
Flow Regulator

Investigation of Variation in the Performance of an Electro Thermal Thruster with Aerospike Nozzle

2016 ◽  
Vol 16 ◽  
pp. 91-103
Author(s):  
Pranav Menon
Keyword(s):  
Electric Propulsion ◽  
Specific Impulse ◽  
Velocity Variation ◽  
Propulsion Systems ◽  
Exit Velocity ◽  
Hot Plasma ◽  
Exit Nozzle ◽  
Ion Propulsion ◽  
Aerospike Nozzle ◽  
Chemical Propulsion

One of the most recently developed modes of propulsion is electric propulsion. The commonly used chemical propulsion systems have the advantage of a high Specific Impulse as compared to that of ion propulsion systems. However, owing to the efficacy of ion propulsion systems, it is considered the future of space exploration.Electro thermal thrusters produce thrust by using electrical fields to force hot plasma out of the nozzle with certain exit velocity. The plasma’s exit velocity and the system’s thrust capacity, as of now, are insufficient for space travel to be conducted within a reasonable time. I intend to study the possibility of improving the thruster’s performance by using an aerospike nozzle as an exit nozzle which meets the conditions required for the thruster to function appropriately. I shall be studying the plasma plume exit velocity variation with respect to the nozzles used. Also, a thermal analysis will be conducted in order to find the correct material for the nozzle.

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