AbstractSeveral reasons justify the development of an ion propulsion system thrust vectoring system. Spacecraft launched to date have used ion thrusters mounted on gimbals to control the thrust vector within a range of about ±5°. Such devices have large mass and dimensions, hence the need exists for a more compact system, preferably mounted within the thruster itself. Since the 1970s several thrust vectoring systems have been developed, with the translatable accelerator grid electrode being considered the most promising. Laboratory models of this system have already been built and successfully tested, but there is still room for improvement in their mechanical design. This work aims to investigate possibilities of refining the design of such movable grid thrust vectoring systems. Two grid suspension designs and three types of actuators were evaluated. The actuators examined were a micro electromechanical system, a NanoMuscle shape memory alloy actuator and a piezoelectric driver. Criteria used for choosing the best system included mechanical simplicity (use of the fewest mechanical parts), accuracy, power consumption and behaviour in space conditions. Designs of systems using these actuators are proposed. In addition, a mission to Mercury using the system with piezoelectric drivers has been modelled and its performance presented.
Design of an ion thruster movable grid thrust vectoring system
Acta Astronautica ; 55 , 3-9 ; 421-432
2004-01-01
12 pages
Article (Journal)
Electronic Resource
English
Design of an ion thruster movable grid thrust vectoring system
British Library Conference Proceedings | 2004
|Design of an ion thruster movable grid thrust vectoring system
Online Contents | 2004
|Ion Thruster Thrust Vectoring by Ion Beam Deflection
British Library Conference Proceedings | 2004
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