Abstract
AbstractElectric propulsion is highly efficient for both deep‐space and near‐earth applications and it is an excellent candidate for small satellites. A colloidal electrostatic thruster for small spacecrafts is investigated in the present paper. A multi‐disciplinary approach (encompassing several scales of modelling: fluid, particle trajectory and molecular modelling) is adopted in order to gain an increased understanding of complex underlying physical processes. The governing factors are accessed in order to obtain the onset and maintenance of a focused beam of droplets or ions. The trajectories and characteristics of the droplets and ions are investigated and multi‐electrode configurations are parameterized by simulations. The flow from the capillary needle, just before the droplets are formed, is also investigated by fluid methods. The molecular modelling provides interesting information on the different modes of emission from the perspective of the stability of the ions. The multi‐scale results obtained are fully discussed and the valuable insights provided by the simulations are also currently fully helping in the design of a laboratory model of an electric micro‐propulsion system for small spacecrafts. magnified image
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
