Orbital maneuvering of microsatellite and nanosatellite requirements can be efficiently addressed by planar nozzles, in which real-time thrust control is gained actuating on the nozzle throat area. In the present work, the method of characteristics is used to design a hypersonic contour; then, the resulting profile is laser cut, assembled, and built into a propulsion system to finally perform tests in a vacuum chamber under several working conditions. Results are used to validate the profile and modeling assumptions and investigate overall behavior. Tests showed that thrust-inlet pressure ratio is a linear function of separation between nozzle contours and that no additional losses are introduced in the system. The corresponding design/manufacture/assembly tools can be used to a provide low-cost/low-weight controllable propulsion systems to the small-satellite industry with no efficiency loss.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Planar Nozzles for Controllable Microthrusters


    Contributors:

    Published in:

    Publication date :

    2016-12-02




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown



    Planar Nozzles for Controllable Microthrusters

    Pedreira, P. H | Online Contents | 2016


    Planar Nozzles for Controllable Microthrusters

    Pedreira, P. H | Online Contents | 2017


    Subliming Solid Microthrusters

    Online Contents | 1998


    Indium Field Emission Microthrusters

    Ruedenauer, F. G. / Fehringer, M. / Steiger, W. | British Library Online Contents | 1997


    Electric microthrusters make it.

    Isley, W. C. / Mickelsen, W. R. | NTRS | 1968